1CGS Popular Post Han 20714 Posted November 5, 2016 1CGS Popular Post Share Posted November 5, 2016 Hello everyone! At one time, in the 123 th edition of Developer Diaries, we published actual (at the time) Aircraft Specs, presented in the IL-2 Sturmovik. However, the time is coming, when new data appearing we make some adjustments of the aircraft aerodynamics and engines, which causes some changes in certain characteristics, usually minor. However, in this way, it is necessary to inform you about the current data on the aircraft. We always do this in the game where you can see the data for each aircraft before your flight. But we also found it necessary to create a special thread here on forum, where you will always find the relevant data on all aircraft without going into the game. We also recommend to pay attention to the new section "Operation features" which we have added for all aircrafts. Airplanes of "Battle of Moscow": I-16 type 24 Indicated stall speed in flight configuration: 143..164 km/h Indicated stall speed in takeoff/landing configuration: 142..163 km/h Dive speed limit: 620 km/h Maximum load factor: 12 G Stall angle of attack in flight configuration: 17.6 ° Stall angle of attack in landing configuration: 15 ° Maximum true air speed at sea level, engine mode - Boosted: 448 km/h Maximum true air speed at 1800 m, engine mode - Nominal: 460 km/h Maximum true air speed at 4500 m, engine mode - Nominal: 490 km/h Service ceiling: 10500 m Climb rate at sea level: 16.7 m/s Climb rate at 3000 m: 13.8 m/s Climb rate at 6000 m: 8.8 m/s Maximum performance turn at sea level: 19.0 s, at 230 km/h IAS. Maximum performance turn at 3000 m: 25.3 s, at 230 km/h IAS. Flight endurance at 3000 m: 0.9 h, at 350 km/h IAS. Takeoff speed: 145..175 km/h Glideslope speed: 185..195 km/h Landing speed: 135..145 km/h Landing angle: 15.3 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates and turn times are given for Boosted power. Engine: Model: M-63 Maximum power in Boosted mode at sea level: 1100 HP Maximum power in Nominal mode at sea level: 930 HP Maximum power in Nominal mode at 1800 m: 1000 HP Maximum power in Nominal mode at 4500 m: 900 HP Engine modes: Nominal (unlimited time): 2200 RPM, 915 mm Hg Boosted power (up to 5 minutes): 2300 RPM, 1065 mm Hg Oil rated temperature in engine output: 55..90 °C Oil maximum temperature in engine output: 125 °C Cylinder head rated temperature: 120..200 °C Cylinder head maximum temperature: 205 °C Supercharger gear shift altitude: 3000 m Empty weight: 1501 kg Minimum weight (no ammo, 10% fuel): 1633 kg Standard weight: 1878 kg Maximum takeoff weight: 2146 kg Fuel load: 191 kg / 260 l Useful load: 645 kg Forward-firing armament: 2 x 7.62mm machine gun "ShKAS", 500 rounds, 1800 rounds per minute, synchronized 2 x 7.62mm machine gun "ShKAS", 900 rounds, 1800 rounds per minute, wing-mounted 2 x 20mm gun "SsVAK", 90 rounds, 800 rounds per minute, wing-mounted (modification) Bombs: 2 x 50 kg general purpose bombs "FAB-50sv" 2 x 104 kg general purpose bombs "FAB-100M" Rockets: Up to 6 x 7 kg rockets "ROS-82", HE payload mass 2.52 kg Length: 6.04 m Wingspan: 9 m Wing surface: 14.54 m^2 Combat debut: June 1941 Additional airplane configurations list: ShVAK 20mm wing-mounted guns with 90 rounds per each instead of default ShKAS wing-mounted machineguns Additional mass: 40 kg Ammunition mass: 22 kg Guns mass: 98 kg Estimated speed loss: 3 km/h 2 x 50 kg General Purpose Bombs FAB-50sv / 2 x 104 kg General Purpose Bombs FAB-100M FAB-50sv: Additional mass: 120 kg Ammo mass: 104 kg Racks mass: 20 kg Estimated speed loss before drop: 13 km/h Estimated speed loss after drop: 7 km/h FAB-100M: Additional mass: 228 kg Ammo mass: 208 kg Racks mass: 20 kg Estimated speed loss before drop: 18 km/h Estimated speed loss after drop: 7 km/h 4 x 82mm High Explosive unguided rockets ROS-82 Additional mass: 40 kg Ammunition mass: 28 kg Racks mass: 12 kg Estimated speed loss before launch: 10 km/h Estimated speed loss after launch: 7 km/h 6 x 82mm High Explosive unguided rockets ROS-82 Additional mass: 60 kg Ammunition mass: 42 kg Racks mass: 18 kg Estimated speed loss before launch: 15 km/h Estimated speed loss after launch: 10 km/h One-piece frontal canopy section for better visibility Additional mass: 0 kg Estimated speed loss: 0 km/h Operation features: - Engine has a boost mode. To set boost mode it is necessary to push the boost lever fully forward and increase the engine to 2300 RPM. - Engine has a two-stage mechanical supercharger which should be manually shifted at 3000m altitude. - Engine mixture control is automatic when the mixture lever is set to maximum. It is possible to manually lean the mixture by moving the mixture control to less than maximum. This also reduces fuel consumption during flight. - Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM. - Oil radiator shutter and air cooling intake shutters control is manual. - Airplane has no flight-control trimmers. Airplane is equipped with bendable trim tabs that can be set pre-flight by ground personnel. - Airplane has a manual system for landing flaps and gear, for this reason it is necessary to extend landing flaps and gear before final approach. Landing flaps can be extended to any angle up to 53°. - Airplane has a tail wheel control mechanism which is linked to rudder pedals. Because of this, it is necessary to avoid of large rudder pedal inputs when moving at high speed on the ground. - Airplane has independent left and right mechanical wheel brakes. To brake it is necessary to push upper part of the rudder pedal. - Airplane has a hydrostatic fuel gauge which shows total fuel remaining only when manual sucker lever is pushed in. In game this happens by itself during horizontal flight by every 10 seconds. - Cockpit has side-doors which should be closed before takeoff to prevent damage. - When bombs are installed there is a salvo controller, it has two release modes: single drop or drop two in a salvo. - When rockets are installed there is a salvo controller, it has three launch modes: single fire, fire two in a salvo or fire by four in a salvo. - The gunsight has a sliding sun-filter. There is also a back-up folding mechanical sight which can be used if main sight is damaged. MiG-3 series 24 Indicated stall speed in flight configuration: 159..175 km/h Indicated stall speed in takeoff/landing configuration: 134..147 km/h Dive speed limit: 750 km/h Maximum load factor: 12.8 G Stall angle of attack in flight configuration: 17.3 ° Stall angle of attack in landing configuration: 15.1 ° Maximum true air speed at sea level, engine mode - Boosted: 525 km/h Maximum true air speed at sea level, engine mode - Nominal: 493 km/h Maximum true air speed at 7600 m, engine mode - Nominal: 626 km/h Service ceiling: 11800 m Climb rate at sea level: 15.9 m/s Climb rate at 3000 m: 14.0 m/s Climb rate at 6000 m: 10.2 m/s Maximum performance turn at sea level: 22.4 s, at 270 km/h IAS. Maximum performance turn at 3000 m: 28.7 s, at 270 km/h IAS. Flight endurance at 3000 m: 2.5 h, at 350 km/h IAS. Takeoff speed: 180..200 km/h Glideslope speed: 195..205 km/h Landing speed: 135..145 km/h Landing angle: 15 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates and turn times are given for Boosted power. Engine: Model: AM-35a Maximum power in Boosted mode at sea level: 1350 HP Maximum power in Nominal mode at sea level: 1120 HP Maximum power in Nominal mode at 6000 m: 1200 HP Engine modes: Nominal (unlimited time): 2050 RPM, 1040 mm Hg Boosted power (up to 10 minutes): 2050 RPM, 1240 mm Hg Water rated temperature in engine output: 80..110 °C Water maximum temperature in engine output: 120 °C Oil rated temperature in engine intake: 40..80 °C Oil maximum temperature in engine intake: 85 °C Oil rated temperature in engine output: 115 °C Oil maximum temperature in engine output: 120 °C Supercharger gear shift altitude: single gear Empty weight: 2650 kg Minimum weight (no ammo, 10% fuel): 2831 kg Standard weight: 3244 kg Maximum takeoff weight: 3476 kg Fuel load: 352 kg / 480 l Useful load: 826 kg Forward-firing armament: 2 x 7.62mm machine gun "ShKAS", 750 rounds, 1800 rounds per minute, synchronized 12.7mm machine gun "UB", 300 rounds, 1000 rounds per minute, synchronized 2 x 12.7mm machine gun "UB", 145 rounds, 1000 rounds per minute, wing-mounted (modification) 2 x 12.7mm machine gun "UB", 350 rounds, 1000 rounds per minute, synchronized (modification) 2 x 20mm gun "SsVAK", 150 rounds, 800 rounds per minute, synchronized (modification) Bombs: 2 x 50 kg general purpose bombs "FAB-50sv" 2 x 104 kg general purpose bombs "FAB-100M" Rockets: 6 x 7 kg rockets "ROS-82", HE payload mass 2.52 kg Length: 8.255 m Wingspan: 10.2 m Wing surface: 17.44 m^2 Combat debut: July 1941 Additional airplane configurations list: BK 12.7mm machineguns in wing-mounted gun pods with 145 rounds per each Additional mass: 155 kg Ammunition mass: 54 kg Guns mass: 101 kg Estimated speed loss: 13 km/h BS 12.7mm nose-mounted machineguns with 350 rounds per each instead of default ShKAS and BS nose-mounted machineguns Additional mass: 34 kg Ammunition mass: 131 kg Guns mass: 62 kg Estimated speed loss: 0 km/h ShVAK 20mm nose-mounted guns with 150 rounds per each instead of default ShKAS and BS nose-mounted machineguns Additional mass: 4 kg Ammunition mass: 69 kg Guns mass: 94 kg Estimated speed loss: 0 km/h 2 x 50 kg General Purpose Bombs FAB-50sv / 2 x 104 kg General Purpose Bombs FAB-100M FAB-50sv: Additional mass: 120 kg Ammunition mass: 104 kg Racks mass: 20 kg Estimated speed loss before drop: 20 km/h Estimated speed loss after drop: 12 km/h FAB-100M: Additional mass: 228 kg Ammunition mass: 208 kg Racks mass: 20 kg Estimated speed loss before drop: 27 km/h Estimated speed loss after drop: 12 km/h 6 x 82mm High Explosive unguided rockets ROS-82 Additional mass: 60 kg Ammunition mass: 42 kg Racks mass: 18 kg Estimated speed loss before launch: 23 km/h Estimated speed loss after launch: 17 km/h Operation features: - Engine has a boost mode which is engaged by setting the mixture control lever to maximum. - Engine has a single-stage mechanical supercharger which does not require manual control. - Engine mixture control is automatic when the mixture lever is set to the intermediate (50%) position. It is possible to manually lean the mixture by setting the control to less than 50%. This will reduce fuel consumption during flight. - Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM. - Water and oil radiator shutter control is manual. - Airplane has only the pitch and yaw flight-control trimmers. - Airplane has automatic wing slats. They deploy when the high angle of attack increases which makes pre-stall softer. - Landing flaps have a limiter for the maximum angle. The flaps have an extended range from 0° to 50°. The landing flaps have pneumatic actuator. Flaps can only be instantly extended to the angle which is set by limiter, gradual extending is impossible. Due to weak force of the actuator the extended landing flaps may retract upward by the airflow when the airspeed is more than 220 km/h. For this reason, it is necessary to remember that flaps will not extend fully in case of high speed. In case of a high-speed landing approach the flaps may extend a few steps right before landing. - Airplane has a tailwheel control system which is unlocked and made controllable by the rudder if the rudder pedal is pressed more than for 40% of its range. The tailwheel remans locked if pedals are deflected less than 40%. Because of this, it is necessary to avoid large rudder pedal inputs when moving at high speed, or be ready to control the airplane with an unlocked tailwheel should large rudder inputs be made. - Airplane has differential pneumatic wheel brakes with shared control lever. This means that if the brake lever is held and the rudder pedal the opposite wheel brake is gradually released causing the plane to swing to one side or the other. - Airplane has a fuel gauge which shows total fuel remaining. - It is impossible to open or close the canopy at high speed due to strong airflow. The canopy has no emergency release, so bail out requires the speed drop before it. - When bombs are installed a salvo controller can be used, it has two release modes: single drop or drop two in a salvo. - When rockets are installed a salvo controller can be used, it has three launch modes: single fire, fire two in a salvo or fire four in a salvo. Il-2 model of 1941 Indicated stall speed in flight configuration: 136..156 km/h Indicated stall speed in takeoff/landing configuration: 128..146 km/h Dive speed limit: 570 km/h Maximum load factor: 11.5 G Stall angle of attack in flight configuration: 19.4 ° Stall angle of attack in landing configuration: 17.5 ° Maximum true air speed at sea level, engine mode - Boosted: 430 km/h Maximum true air speed at sea level, engine mode - Nominal (at 2150 RPM): 421 km/h Maximum true air speed at 2500 m, engine mode - Nominal (at 2150 RPM): 455 km/h Service ceiling: 7500 m Climb rate at sea level: 9.4 m/s Climb rate at 3000 m: 8.9 m/s Climb rate at 6000 m: 3.9 m/s Maximum performance turn at sea level: 23.1 s, at 250 km/h IAS. Maximum performance turn at 3000 m: 32.6 s, at 250 km/h IAS. Flight endurance at 3000 m: 1.7 h, at 300 km/h IAS. Takeoff speed: 150..190 km/h Glideslope speed: 185..195 km/h Landing speed: 130..140 km/h Landing angle: 11.7 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates are given for Nominal power, turn times are given for Boosted power. Engine: Model: AM-38 Maximum power in Boosted mode at sea level: 1600 HP Maximum power in Nominal mode at sea level: 1500 HP Maximum power in Nominal mode at 1650 m: 1500 HP Engine modes: Nominal (unlimited time): 2050 RPM, 1180 mm Hg Boosted power (up to 10 minutes): 2150 RPM, 1280 mm Hg Water rated temperature in engine output: 80..110 °C Water maximum temperature in engine output: 120 °C Oil rated temperature in engine intake: 40..80 °C Oil maximum temperature in engine intake: 85 °C Oil rated temperature in engine output: 115 °C Oil maximum temperature in engine output: 120 °C Supercharger gear shift altitude: single gear Empty weight: 4242 kg Minimum weight (no ammo, 10% fuel): 4464 kg Standard weight: 5049 kg Maximum takeoff weight: 5888 kg Fuel load: 470 kg / 641 l Useful load: 1646 kg Forward-firing armament: 2 x 20mm gun "SsVAK", 210 rounds, 800 rounds per minute, wing-mounted 2 x 7.62mm machine gun "ShKAS", 750 rounds, 1800 rounds per minute, wing-mounted 2 x 23mm gun "VYa-23", 150 rounds, 600 rounds per minute, wing-mounted (modification) Bombs: Up to 6 x 50 kg general purpose bombs "FAB-50sv" Up to 6 x 104 kg general purpose bombs "FAB-100M" 2 x 254 kg general purpose bombs "FAB-250sv" Rockets: 8 x 7 kg rockets "ROS-82", HE payload mass 2.5 kg 8 x 15 kg rockets "RBS-82", HEAT payload mass 7.2 kg 8 x 42 kg rockets "ROFS-132", HE payload mass 21.3 kg Length: 11.5 m Wingspan: 14.6 m Wing surface: 38.5 m^2 Combat debut: June 1941 Additional airplane configurations list: 2 VYa-23 23mm wing-mounted guns with 150 rounds per each Additional mass: 110 kg Ammunition mass: 170 kg Guns mass: 132 kg Estimated speed loss: 1 km/h 6 x 50 kg General Purpose Bombs FAB-50sv / 6 x 104 kg General Purpose Bombs FAB-100M FAB-50sv: Additional mass: 300 kg Ammunition mass: 300 kg Estimated speed loss before drop: 5 km/h Estimated speed loss after drop: 0 km/h FAB-100M: Additional mass: 624 kg Ammunition mass: 624 kg Estimated speed loss before drop: 9 km/h Estimated speed loss after drop: 0 km/h 2 x 254 kg General Purpose Bombs FAB-250sv Additional mass: 538 kg Ammunition mass: 508 kg Racks mass: 30 kg Estimated speed loss before drop: 19 km/h Estimated speed loss after drop: 9 km/h 8 x 82mm Armour Piercing unguided rockets RBS-82 Additional mass: 144 kg Ammunition mass: 120 kg Racks mass: 24 kg Estimated speed loss before launch: 13 km/h Estimated speed loss after launch: 8 km/h 8 x 132mm High Explosive unguided rockets ROFS-132 Additional mass: 376 kg Ammunition mass: 336 kg Racks mass: 40 kg Estimated speed loss before launch: 20 km/h Estimated speed loss after launch: 12 km/h Operation features: - Engine has a boost mode which is engaging by setting mixture control lever to maximum position. - Engine has a single stage mechanical supercharger which does not require manual control. - Engine mixture control is automatic when the mixture lever is set to the intermediate (50%) position. It is possible to manually lean the mixture by moving the control lever to less than 50%. This will lower fuel consumption during flight. - Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM. - Water and oil radiator shutter control is manual. Airplane has armored oil radiator shutters which should to be closed on start of ground attack to reduce possibility of combat damage. After finishing the attack, it is necessary to re-open the shutters to the required position. - Airplane has only the pitch flight-control trimmer. - Landing flaps have a pneumatic actuator. Flaps can only be fully extended; gradual extending is impossible. Due to the weak force of the actuator the extended landing flaps may be pressed upwards by the airflow if the airspeed is more than 220 km/h. Remember that the flaps will not extend fully in case of high speed. In case of a high-speed landing approach the flaps may extend a few steps further right before landing. - Airplane has a manual tail wheel lock. Wheel should be locked when taxiing straight for a long distance and before takeoff and landing. - Airplane has differential pneumatic wheel brakes with shared control lever. This means that if the brake lever is held and the rudder pedal the opposite wheel brake is gradually released causing the plane to swing to one side or the other. - Airplane has a fuel gauge which shows the amount of remaining fuel in the front or bottom fuel tank depending on the switch position. In game the fuel indication switch changes by itself during horizontal flight by every 10 seconds. Rear fuel tank level is not indicated. - Cockpit canopy weight is 50 kg and it has no lock in the open position, for this reason the canopy may to spontaneously close in a deep dive. Also, it is impossible to open or close canopy at high speed due to strong airflow. The canopy has no emergency release, so bail out requires the speed drop before it. - Airplane is equipped with a joint salvo controller both for bombs and rockets, it has three release/fire modes: single launch, launch two in a salvo or launch four in a salvo. - The gunsight is installed on a sliding bar which allows the pilot to extend the gunsight towards the pilot allowing fo an increase in the field of view through the gunsight. Pe-2 series 35 Indicated stall speed in flight configuration: 175..200 km/h Indicated stall speed in takeoff/landing configuration: 148..169 km/h Dive speed limit: 790 km/h Maximum load factor: 11 G Stall angle of attack in flight configuration: 13.9 ° Stall angle of attack in landing configuration: 9.8 ° Maximum true air speed at sea level, engine mode - Nominal: 434 km/h Maximum true air speed at 2000 m, engine mode - Nominal: 476 km/h Maximum true air speed at 5000 m, engine mode - Nominal: 521 km/h Service ceiling: 9100 m Climb rate at sea level: 9.3 m/s Climb rate at 3000 m: 8.4 m/s Climb rate at 6000 m: 5.6 m/s Maximum performance turn at sea level: 30.5 s, at 270 km/h IAS. Maximum performance turn at 3000 m: 39.9 s, at 270 km/h IAS. Flight endurance at 3000 m: 3.7 h, at 300 km/h IAS. Takeoff speed: 160..200 km/h Glideslope speed: 220..240 km/h Landing speed: 155..165 km/h Landing angle: 12.5 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates and turn times are given for Nominal power. Engine: Model: M-105RA Maximum power in Nominal mode at sea level: 1020 HP Maximum power in Nominal mode at 2000 m: 1100 HP Maximum power in Nominal mode at 4000 m: 1050 HP Engine modes: Nominal (unlimited time): 2700 RPM, 910 mm Hg Water rated temperature in engine output: 70..85 °C Water maximum temperature in engine output: 100 °C Oil rated temperature in engine output: 90..100 °C Oil maximum temperature in engine output: 110 °C Supercharger gear shift altitude: 2700 m Empty weight: 6078 kg Minimum weight (no ammo, 10% fuel): 6640 kg Standard weight: 7697 kg Maximum takeoff weight: 8712 kg Fuel load: 1129 kg / 1505 l Useful load: 2634 kg Forward-firing armament: 12.7mm machine gun "UB", 150 rounds, 1000 rounds per minute, nose-mounted 7.62mm machine gun "ShKAS", 450 rounds, 1800 rounds per minute, nose-mounted Defensive armament: Top: 7.62mm machine gun "ShKAS", 750 rounds, 1800 rounds per minute Belly: 12.7mm machine gun "UB", 200 rounds, 1000 rounds per minute Side: 7.62mm machine gun "ShKAS", 225 rounds, 1800 rounds per minute Bombs: Up to 10 x 104 kg general purpose bombs "FAB-100M" Up to 4 x 254 kg general purpose bombs "FAB-250sv" Up to 2 x 512 kg general purpose bombs "FAB-500M" Rockets: 10 x 23 kg rockets "ROS-132", HE payload mass 9.1 kg Length: 12.69 m Wingspan: 17.12 m Wing surface: 40.8 m^2 Combat debut: July 1941 Additional airplane configurations list: 10 x 104 kg General Purpose Bombs FAB-100M Additional mass: 1040 kg Ammunition mass: 1040 kg Estimated speed loss before drop: 23 km/h Estimated speed loss after drop: 0 km/h 4 x 254 kg General Purpose Bombs FAB-250sv Additional mass: 1016 kg Ammunition mass: 1016 kg Estimated speed loss before drop: 33 km/h Estimated speed loss after drop: 0 km/h 2 x 512 kg General Purpose Bombs FAB-500M Additional mass: 1024 kg Ammunition mass: 1024 kg Estimated speed loss before drop: 48 km/h Estimated speed loss after drop: 0 km/h 10 x 132mm High Explosive unguided rockets ROS-132 Additional mass: 280 kg Ammunition mass: 230 kg Racks mass: 50 kg Estimated speed loss before launch: 31 km/h Estimated speed loss after launch: 20 km/h RPK-2 fixed loop radio compass for navigation with radio beacons Additional mass: 20 kg Estimated speed loss: 2 km/h Operation features: - Engine has a two-stage mechanical supercharger which must be manually switched at 2700m altitude. - Engine mixture control is manual; it is necessary to lean the mixture if altitude is more than 3-4 km for optimal engine operation. Also, leaning the mixture allows a reduction in fuel consumption during flight. - Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM. The governor is electrically actuated and takes a long time to reach the required revolutions, up to 45 seconds when going from minimum to maximum. - Water and oil radiator shutter control is manual. - Airplane has trimmers for all flight-controls: pitch, roll, yaw. - Airplane has fence-type airbrakes which are located under the wing and used to slow the descent during steep dive bombing. - Landing flaps have electro-hydraulic actuator and they can be extended to any angle up to 50°. When landing and the flaps are fully extended the angle of attack for a stall is less than landing pitch angle. For this reason, it is prohibited to extend flaps to more than to 35° (70%) on landing. - Airplane has automatically controlled horizontal stabilizer. The automatic control system adjusts the stabilizer angle depending on landing flaps extended angle. - Airplane tail wheel rotates freely and does not have a lock. For this reason, it is necessary to confidently and accurately operate the rudder pedals during the takeoff and landing. - Airplane has differential pneumatic wheel brakes with shared control lever. This means that if the brake lever is held and the rudder pedal the opposite wheel brake is gradually released causing the plane to swing to one side or the other. - Airplane has three fuel gauges which shows the level in the fuselage fuel tank, left wing tanks and right wing tanks. - Cockpit canopy have an emergency release system for bailouts. - Airplane is equipped with a bomb salvo controller, it has four release modes: drop single, drop two in a salvo, drop four in a salvo or drop all bombs in salvo. There is also a controller for a drop delay between each bomb in the salvo. - When rockets are installed a salvo controller can be used, it has three launch modes: single fire, fire two in a salvo or fire four in a salvo. Aircraft has a fire control system that is designed for eight rockets. However, for added punch, ten rockets were typically loaded. In that case, the ninth rocket will fire with the seventh and the tenth will fire with the eighth. Bf 109 E-7 Indicated stall speed in flight configuration: 152..159 km/h Indicated stall speed in takeoff/landing configuration: 147..146 km/h Dive speed limit: 850 km/h Maximum load factor: 11 G Stall angle of attack in flight configuration: 20 ° Stall angle of attack in landing configuration: 16.6 ° Maximum true air speed at sea level, engine mode - Emergency: 477 km/h Maximum true air speed at 2000 m, engine mode - Emergency: 520 km/h Maximum true air speed at 5000 m, engine mode - Emergency: 564 km/h Service ceiling: 10500 m Climb rate at sea level: 14 m/s Climb rate at 3000 m: 13.3 m/s Climb rate at 6000 m: 7 m/s Maximum performance turn at sea level: 20.5 s, at 270 km/h IAS. Maximum performance turn at 3000 m: 25.5 s, at 270 km/h IAS. Flight endurance at 3000 m: 2.2 h, at 350 km/h IAS. Takeoff speed: 140..170 km/h Glideslope speed: 180..190 km/h Landing speed: 130..140 km/h Landing angle: 14.3 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates are given for Combat power, turn times are given for Boosted power. Engine: Model: DB-601A Maximum power in Boosted mode at sea level: 1100 HP Maximum power in Emergency mode at sea level: 990 HP Maximum power in Emergency mode at 4500 m: 1020 HP Maximum power in Combat mode at sea level: 910 HP Maximum power in Combat mode at 5000 m: 960 HP Engine modes: Nominal (unlimited time): 2200 RPM, 1.15 ata Combat power (up to 30 minutes): 2300 RPM, 1.23 ata Emergency power (up to 5 minutes): 2400 RPM, 1.3 ata Boosted power (up to 1 minute): 2400 RPM, 1.4 ata Water rated temperature in engine output: 94 °C Water maximum temperature in engine output: 100 °C Oil rated temperature in engine intake: 30..75 °C Oil maximum temperature in engine intake: 80 °C Oil rated temperature in engine output: 95 °C Oil maximum temperature in engine output: 105 °C Supercharger gear shift altitude: fluid coupling Empty weight: 2049 kg Minimum weight (no ammo, 10% fuel): 2340 kg Standard weight: 2614 kg Maximum takeoff weight: 2893 kg Fuel load: 304 kg / 400 l Useful load: 844 kg Forward-firing armament: 2 x 20mm gun "MG FF", 60 rounds, 540 rounds per minute, wing-mounted 2 x 7.92mm machine gun "MG 17", 1000 rounds, 1200 rounds per minute, synchronized Bombs: Up to 4 x 55 kg general purpose bombs "SC 50" 249 kg general purpose bomb "SC 250" Length: 8.8 m Wingspan: 9.9 m Wing surface: 16.4 m^2 Combat debut: August 1940 Additional airplane configurations list: 4 x 55 kg General Purpose Bombs SC 50 Additional mass: 260 kg Ammunition mass: 220 kg Racks mass: 40 kg Estimated speed loss before drop: 53 km/h Estimated speed loss after drop: 13 km/h 249 kg General Purpose Bomb SC 250 Additional mass: 279 kg Ammunition mass: 249 kg Racks mass: 30 kg Estimated speed loss before drop: 34 km/h Estimated speed loss after drop: 11 km/h Removed pilot armoured headrest for improved field of view Weight savings: 8 kg Estimated speed loss: 0 km/h Additional pilot protection: armoured triplex wind screen Additional mass: 20 kg Estimated speed loss: 1 km/h Additional protection: armoured plates on bottom of plane Additional mass: 89 kg Estimated speed loss: 4 km/h Operation features: - Airplane has a wide automatization of the engine systems, in fact, to control speed it is only necessary to use the throttle lever. There is no need to manually set engine revolutions and mixture or supercharger gear in normal flight. - To reduce swinging during taxiing due to prop-wash the propeller pitch control should be switched to manual mode and pitch should be reduced to minimum. - Water and oil radiator shutters are controlled manually. - Airplane has no flight-control trimmers. Airplane is equipped with bendable trim tabs that can be set pre-flight by ground personnel. - Airplane has a manually controlled horizontal stabilizer. It should be set to +1° before takeoff and to -4°...-5° before landing. Also, it may be used to trim the flight stick during the flight. In a deep dive the stabilizer should be set so that the pilot must push the flight stick forward to maintain the dive angle. - Airplane has automatic wing slats. They deploy when the high angle of attack increases which makes pre-stall softer. - Airplane has a manual mechanical system for retracting the landing flaps, for this reason it is necessary to extend landing flaps well before final approach. Markers on the left-wing flap indicate how far the flaps are extended. The flaps can be extended to any angle up to 42°. - Airplane has a manual tail wheel lock. Wheel should be locked when taxiing straight for a long distance and before takeoff and landing. - Airplane has independent left and right hydraulic wheel brake controls. To apply either brake push the upper part of the rudder pedal. - Airplane has a fuel gauge which shows total fuel remaining. Also, it has an emergency fuel warning light (80 liters). - The design of the cockpit canopy does not allow it to be opened during flight. The canopy should be closed before takeoff to prevent damage. The canopy has an emergency release system for bailouts. - The control system for the bomb rack only allows for dropping bombs one by one. - The gunsight has a sliding sun-filter. Bf 109 F-2 Indicated stall speed in flight configuration: 151..168 km/h Indicated stall speed in takeoff/landing configuration: 144 km/h..159 km/h Dive speed limit: 850 km/h Maximum load factor: 11 G Stall angle of attack in flight configuration: 19.7 ° Stall angle of attack in landing configuration: 17 ° Maximum true air speed at sea level, engine mode - Emergency: 528 km/h Maximum true air speed at 2000 m, engine mode - Emergency: 563 km/h Maximum true air speed at 5000 m, engine mode - Emergency: 606 km/h Service ceiling: 11500 m Climb rate at sea level: 16.4 m/s Climb rate at 3000 m: 14.1 m/s Climb rate at 6000 m: 10 m/s Maximum performance turn at sea level: 23.6 s, at 270 km/h IAS. Maximum performance turn at 3000 m: 29.0 s, at 270 km/h IAS. Flight endurance at 3000 m: 2.4 h, at 350 km/h IAS. Takeoff speed: 145..175 km/h Glideslope speed: 185..195 km/h Landing speed: 135..145 km/h Landing angle: 14.8 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates are given for Combat power, turn times are given for Boosted power. Engine: Model: DB-601N Maximum power in Boosted mode at 5500 m: 1220 HP Maximum power in Emergency mode at sea level: 1175 HP Maximum power in Emergency mode at 4900 m: 1175 HP Maximum power in Combat mode at sea level: 1015 HP Maximum power in Combat mode at 4900 m: 1045 HP Engine modes: Nominal (unlimited time): 2300 RPM, 1.15 ata Combat power (up to 30 minutes): 2400 RPM, 1.25 ata Emergency power (up to 3 minutes): 2600 RPM, 1.35 ata Boosted power (up to 1 minute): 2800 RPM, 1.42 ata Water rated temperature in engine output: 100..102 °C Water maximum temperature in engine output: 110 °C Oil rated temperature in engine intake: 70..80 °C Oil maximum temperature in engine intake: 85 °C Supercharger gear shift altitude: fluid coupling Empty weight: 2171 kg Minimum weight (no ammo, 10% fuel): 2445 kg Standard weight: 2789 kg Maximum takeoff weight: 3092 kg Fuel load: 304 kg / 400 l Useful load: 921 kg Forward-firing armament: 15mm gun "MG 151/15", 200 rounds, 700 rounds per minute, nose-mounted 2 x 7.92mm machine gun "MG 17", 500 rounds, 1200 rounds per minute, synchronized 20mm gun "MG 151/20", 200 rounds, 700 rounds per minute, nose-mounted (modification) Bombs: Up to 4 x 55 kg general purpose bombs "SC 50" 249 kg general purpose bomb "SC 250" Length: 8.94 m Wingspan: 9.97 m Wing surface: 16.1 m^2 Combat debut: March 1941 Additional airplane configurations list: MG 151/20 20mm nose-gun with 200 rounds Additional mass: 4 kg Ammunition mass: 42 kg Gun mass: 44 kg Estimated speed loss: 0 km/h 4 x 55 kg General Purpose Bombs SC 50 Additional mass: 260 kg Ammunition mass: 220 kg Racks mass: 40 kg Estimated speed loss before drop: 51 km/h Estimated speed loss after drop: 11 km/h 249 kg General Purpose Bomb SC 250 Additional mass: 279 kg Ammunition mass: 249 kg Racks mass: 30 kg Estimated speed loss before drop: 31 km/h Estimated speed loss after drop: 10 km/h Removed pilot armoured headrest for improved field of view Weight savings: 8 kg Estimated speed loss: 0 km/h Additional pilot protection: armoured triplex wind screen Additional mass: 20 kg Estimated speed loss: 1 km/h Operation features: - Airplane has a wide automatization of the engine systems, in fact, to control speed it is only necessary to use the throttle lever. There is no need to manually set engine revolutions and mixture or supercharger gear in normal flight. - In addition to full-automatic mode there is a special emergency mode for the radiator shutters, which can be used in specific situations. In this mode, the shutters are forced to be fully opened. - To reduce swinging during taxiing due to prop-wash the propeller pitch control should be switched to manual mode and pitch should be reduced to minimum. - Airplane has no flight-control trimmers. Airplane is equipped with bendable trim tabs that can be set pre-flight by ground personnel. - Airplane has a manually controlled horizontal stabilizer. It should be set to +1° before takeoff and to -4°...-5° before landing. Also, it may be used to trim the flight stick during the flight. In a deep dive the stabilizer should be set so that the pilot must push the flight stick forward to maintain the dive angle. - Airplane has automatic wing slats. They deploy when the high angle of attack increases which makes pre-stall softer. - Airplane has a manual mechanical system for retracting the landing flaps, for this reason it is necessary to extend landing flaps well before final approach. Markers on the left-wing flap indicate how far the flaps are extended. The flaps can be extended to any angle up to 40°. - Airplane has a manual tail wheel lock. Wheel should be locked when taxiing straight for a long distance and before takeoff and landing. - Airplane has independent left and right hydraulic wheel brake controls. To apply either brake push the upper part of the rudder pedal. - Airplane has a fuel gauge which shows total fuel remaining. Also, it has an emergency fuel warning light (80 liters). - The design of the cockpit canopy does not allow it to be opened during flight. The canopy should be closed before takeoff to prevent damage. The canopy has an emergency release system for bailouts. - The control system for the bomb rack only allows for dropping bombs one by one. - The gunsight has a sliding sun-filter. Bf 110 E-2 Indicated stall speed in flight configuration: 148..182 km/h Indicated stall speed in takeoff/landing configuration: 131..162 km/h Dive speed limit: 740 km/h Maximum load factor: 11 G Stall angle of attack in flight configuration: 20.7 ° Stall angle of attack in landing configuration: 17.5 ° Maximum true air speed at sea level, engine mode - Emergency: 456 km/h Maximum true air speed at 2000 m, engine mode - Emergency: 494 km/h Maximum true air speed at 5000 m, engine mode - Emergency: 529 km/h Service ceiling: 9500 m Climb rate at sea level: 10.3 m/s Climb rate at 3000 m: 9.6 m/s Climb rate at 6000 m: 6.1 m/s Maximum performance turn at sea level: 27.4 s, at 270 km/h IAS. Maximum performance turn at 3000 m: 35.4 s, at 270 km/h IAS. Flight endurance at 3000 m: 3.5 h, at 300 km/h IAS. Takeoff speed: 180..220 km/h Glideslope speed: 200..220 km/h Landing speed: 140..160 km/h Landing angle: 10.6 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates are given for Combat power, turn times are given for Boosted power. Engine: Model: DB-601A Maximum power in Boosted mode at sea level: 1100 HP Maximum power in Emergency mode at sea level: 990 HP Maximum power in Emergency mode at 4500 m: 1020 HP Maximum power in Combat mode at sea level: 910 HP Maximum power in Combat mode at 5000 m: 960 HP Engine modes: Nominal (unlimited time): 2200 RPM, 1.15 ata Combat power (up to 30 minutes): 2300 RPM, 1.23 ata Emergency power (up to 5 minutes): 2400 RPM, 1.3 ata Boosted power (up to 1 minute): 2400 RPM, 1.4 ata Water rated temperature in engine output: 94 °C Water maximum temperature in engine output: 100 °C Oil rated temperature in engine intake: 30..75 °C Oil maximum temperature in engine intake: 80 °C Oil rated temperature in engine output: 95 °C Oil maximum temperature in engine output: 105 °C Supercharger gear shift altitude: fluid coupling Empty weight: 5175 kg Minimum weight (no ammo, 10% fuel): 5597 kg Standart weight: 6706 kg Maximum takeoff weight: 8398 kg Fuel load: 965 kg / 1270 l Useful load: 3223 kg Forward-firing armament: 4 x 7.92mm machine gun "MG 17", 1000 rounds, 1200 rounds per minute, nose-mounted 2 x 20mm gun "MG FF", 180 rounds, 540 rounds per minute, nose-mounted Defensive armament: Backward: 7.92mm machine gun "MG 15", 825 rounds, 1000 rounds per minute Bombs: Up to 12 x 55 kg general purpose bombs "SC 50" Up to 2 x 249 kg general purpose bombs "SC 250" Up to 2 x 500 kg general purpose bombs "SC 500" 1090 kg general purpose bomb "SC 1000" Length: 12.1 m Wingspan: 16.3 m Wing surface: 38.4 m^2 Combat debut: October 1940 Additional airplane configurations list: 12 x 55 kg General Purpose Bombs SC 50 Additional mass: 820 kg Ammunition mass: 660 kg Racks mass: 160 kg Estimated speed loss before drop: 80 km/h Estimated speed loss after drop: 38 km/h 2 x 500 kg General Purpose Bomb SC 500 Additional mass: 1025 kg Ammunition mass: 1000 kg Racks mass: 50 kg Estimated speed loss before drop: 35 km/h Estimated speed loss after drop: 5 km/h 1090 kg General Purpose Bomb SC 1000 Additional mass: 1140 kg Ammunition mass: 1090 kg Racks mass: 50 kg Estimated speed loss before drop: 33 km/h Estimated speed loss after drop: 5 km/h Additional pilot protection: armoured triplex wind screen and armoured headrest Additional mass: 32 kg Estimated speed loss: 0 km/h Additional protection: armoured plates on engines and radiators Additional mass: 245 kg Estimated speed loss: 0 km/h Operation features: - Airplane has a wide automatization of the engine systems, in fact, to control speed it is only necessary to use the throttle lever. There is no need to manually set engine revolutions and mixture or supercharger gear in normal flight. - Water and oil radiator shutters are controlled manually. The oil radiator control has five fixed positions. The water radiator control has nine fixed positions. - Propellers have a feathering system which should be activated in case of engine damage to reduce drag of the propeller in auto-rotation. - To reduce swinging during taxiing due to prop-wash it is necessary to use asymmetrical engines thrust. It is recommended to give the left engine 20% more power. Also, the propeller pitch control should be switched to manual mode and pitch should be reduced to minimum. - Airplane has only pitch and yaw flight-control trimmers. - Airplane has automatic wing slats. They deploy when the high angle of attack increases which makes pre-stall softer. - Landing flaps have a hydraulic actuator and they can be extended to any angle up to 50°. - Airplane has a automatically controlled horizontal stabilizer. An automatic control system adjusts the stabilizer angle depending on the extended angle of the landing flaps. - Airplane tail wheel rotates freely and does not have a lock. For this reason, it is necessary to confidently and accurately operate the rudder pedals during the takeoff and landing. - Airplane has independent left and right hydraulic wheel brake controls. To apply either brake push the upper part of the rudder pedal. - Airplane has a fuel gauge which shows the reaming fuel in one of four fuel tanks depending on the switch position. In the game the fuel indicator switch changes by itself during horizontal flight by every 10 seconds. Also, the airplane has a low fuel warning light (50 liters) for each tank. - The design of the cockpit canopy does not allow it to be opened during flight. The canopy should be closed before takeoff to prevent damage. The canopy has an emergency release system for bailouts. - Airplane is equipped with an automatic bomb salvo controller, it allows you to choose which bomb-racks to be released (central belly, left and right wing) and to switch the bomb salvo (single release or release all bombs). - Reloading of both MG-FF guns (forward and rearward) must be performed by the rear gunner. The forward firing MGFF must be reloaded at the pilot's command. - The gunsight has a sliding sun-filter. Ju 88 A-4 Indicated stall speed in flight configuration: 188..205 km/h Indicated stall speed in takeoff/landing configuration: 158..185 km/h Dive speed limit: 670 km/h Maximum load factor: 8.0 G Stall angle of attack in flight configuration: 21.0 ° Stall angle of attack in landing configuration: 16.6 ° Maximum true air speed at sea level, engine mode - Climb: 424 km/h Maximum true air speed at 2000 m, engine mode - Climb: 462 km/h Maximum true air speed at 5000 m, engine mode - Climb: 486 km/h Service ceiling: 7500 m Climb rate at sea level: 7.0 m/s Climb rate at 3000 m: 5.1 m/s Climb rate at 6000 m: 3.4 m/s Maximum performance turn at sea level: 33.0 s, at 250 km/h IAS. Maximum performance turn at 3000 m: 50.5 s, at 250 km/h IAS. Flight endurance at 3000 m: 3.8 h, at 300 km/h IAS. Takeoff speed: 170..210 km/h Glideslope speed: 210..220 km/h Landing speed: 150..160 km/h Landing angle: 9 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates are given for Climb power, turn times are given for Take-off power. Engine: Model: Jumo-211J Maximum power in Take-off mode at sea level: 1420 HP Maximum power in Climb mode at sea level: 1190 HP Maximum power in Climb mode at 1500 m: 1260 HP Maximum power in Climb mode at 4900 m: 1180 HP Engine modes: Nominal (unlimited time): 2250 RPM, 1.15 ata Climb power (up to 30 minutes): 2400 RPM, 1.25 ata Take-off power (up to 1 minute): 2600 RPM, 1.42 ata Water rated temperature in engine output: 80 °C Water maximum temperature in engine output: 110 °C Oil rated temperature in engine output: 100 °C Oil maximum temperature in engine output: 130 °C Supercharger gear shift altitude: automatic Empty weight: 8619 kg Minimum weight (no ammo, 10% fuel): 9458 kg Standard weight: 12110 kg Maximum takeoff weight: 13655 kg Fuel load: 1277 kg / 1680 l Useful load: 5036 kg Defensive armament: Nose: 7.92mm machine gun "MG 81", 750 rounds, 1600 rounds per minute Top: 7.92mm machine gun "MG 81", 1000 rounds, 1600 rounds per minute Belly: 2 x 7.92mm machine gun "MG 81", 950 rounds, 1600 rounds per minute Bombs: Up to 44 x 55 kg general purpose bombs "SC 50" Up to 6 x 249 kg general purpose bombs "SC 250" Up to 4 x 500 kg general purpose bombs "SC 500" Up to 2 x 1090 kg general purpose bombs "SC 1000" 1780 kg general purpose bomb "SC 1800" Length: 14.3 m Wingspan: 20.02 m Wing surface: 52.7 m^2 Combat debut: June 1941 Additional airplane configurations list: 44 x 55 kg General Purpose Bombs SC 50 Additional mass: 2640 kg Ammunition mass: 2420 kg Racks mass: 220 kg Estimated speed loss before drop: 97 km/h Estimated speed loss after drop: 39 km/h 6 x 249 kg General Purpose Bomb SC 250 (+2 on the underwing holders) Additional mass: 1544 kg Ammunition mass: 1494 kg Racks mass: 50 kg Estimated speed loss before drop: 37 km/h Estimated speed loss after drop: 4 km/h 4 x 500 kg General Purpose Bomb SC 500 Additional mass: 2000 kg Ammunition mass: 2000 kg Estimated speed loss before drop: 34 km/h Estimated speed loss after drop: 0 km/h 2 x 1090 kg General Purpose Bomb SC 1000 Additional mass: 2180 kg Ammunition mass: 2180 kg Estimated speed loss before drop: 26 km/h Estimated speed loss after drop: 0 km/h 1780 kg General Purpose Bomb SC 1800 Additional mass: 1780 kg Ammunition mass: 1780 kg Estimated speed loss before drop: 23 km/h Estimated speed loss after drop: 0 km/h Operation features: - Each engine has a two-stage mechanical supercharger with an automatic switch system that switches gears depending altitude and engine revolutions. It can also be manually switched to first gear. - Engine mixture control is automatic. - Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM. - Propellers have a feathering system which should be activated in case of engine damage to reduce drag of the propeller in auto-rotation. - Water and oil radiators shutters are joint with engine cowl outlet shutters and manually operated. Ground personnel may install additional fixed shutters on the intake of the oil radiators in cold weather to prevent freezing of the oil - Airplane has trimmers for all flight-controls: pitch, roll, yaw. - Airplane has fence-type airbrakes which are located under the wing and used to slow the descent during steep dive bombing. - Airplane has hydraulic-actuated landing flaps with three fixed positions: retracted, takeoff (25°) and landing (50°). Flap indicator lights are located on left panel. - Airplane has a automatically controlled horizontal stabilizer. An automatic control system adjusts the stabilizer angle depending on the extended angle of the landing flaps. The stabilizer control lamps are located near the flaps indicator lights. - Airplane is also equipped with differential ailerons which are lowered in synch with the flaps. - Lowering the landing gear takes a long time, for this reason it is necessary to extend the landing gear well before final landing approach. - Airplane tail wheel rotates freely and does not have a lock. For this reason, it is necessary to confidently and accurately operate the rudder pedals during the takeoff and landing. - Airplane has independent left and right hydraulic wheel brake controls. To apply either brake push the upper part of the rudder pedal. - Airplane has dedicated fuel gauges for left and right fuel tank groups and there is a switch between the internal and external fuel tank group indicator. In game the fuel indicator switch changes by itself during horizontal flight every 10 seconds. Also, the airplane has low fuel warning lights (180 liters) for the internal tanks. - Airplane is equipped with an automatic bomb salvo controller, it allows the pilot to switch between the bomb racks to be released (internal or external) and to switch between different salvo quantities. There is also a controller for a drop delay between each bomb in the salvo. Airplanes of "Battle of Stalingrad": LaGG-3 series 29 Indicated stall speed in flight configuration: 163..189 km/h Indicated stall speed in takeoff/landing configuration: 138..168 km/h Dive speed limit: 750 km/h Maximum load factor: 11 G Stall angle of attack in flight configuration: 18 ° Stall angle of attack in landing configuration: 15 ° Maximum true air speed at sea level, engine mode - Nominal: 505 km/h Maximum true air speed at 2000 m, engine mode - Nominal: 548 km/h Maximum true air speed at 4000 m, engine mode - Nominal: 573 km/h Service ceiling: 10500 m Climb rate at sea level: 14.9 m/s Climb rate at 3000 m: 13.3 m/s Climb rate at 6000 m: 8 m/s Maximum performance turn at sea level: 22.2 s, at 280 km/h IAS. Maximum performance turn at 3000 m: 28.9 s, at 270 km/h IAS. Flight endurance at 3000 m: 2.2 h, at 350 km/h IAS. Takeoff speed: 165..200 km/h Glideslope speed: 200..210 km/h Landing speed: 140..160 km/h Landing angle: 12.8 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates and turn times are given for Nominal power. Engine: Model: M-105PF Maximum power in Nominal mode at sea level: 1200 HP Maximum power in Nominal mode at 800 m: 1260 HP Maximum power in Nominal mode at 2700 m: 1200 HP Engine modes: Nominal (unlimited time): 2700 RPM, 1050 mm Hg Water rated temperature in engine output: 70..85 °C Water maximum temperature in engine output: 100 °C Oil rated temperature in engine output: 90..100 °C Oil maximum temperature in engine output: 115 °C Supercharger gear shift altitude: 2500 m Empty weight: 2620 kg Minimum weight (no ammo, 10% fuel): 2773 kg Standard weight: 3157 kg Maximum takeoff weight: 3701 kg Fuel load: 348 kg / 467 l Useful load: 1081 kg Forward-firing armament: 20mm gun "SsVAK", 160 rounds, 800 rounds per minute, nose-mounted 12.7mm machine gun "UB", 200 rounds, 1000 rounds per minute, synchronized 23mm gun "VYa-23", 90 rounds, 600 rounds per minute, nose-mounted (modification) 37mm gun "Sh-37", 20 rounds, 185 rounds per minute, nose-mounted (modification) Bombs: 2 x 50 kg general purpose bombs "FAB-50sv" 2 x 104 kg general purpose bombs "FAB-100M" Rockets: 6 x 7 kg rockets "ROS-82", HE payload mass 2.52 kg Length: 8.84 m Wingspan: 9.8 m Wing surface: 17.51 m^2 Combat debut: May 1942 Additional airplane configurations list: VYa-23 23mm motor-gun with 90 rounds Additional mass: 35 kg Ammunition mass: 45 kg Gun mass: 66 kg Estimated speed loss: 0 km/h Sh-37 37mm motor-gun with 20 rounds Additional mass: 106 kg Ammunition mass: 25 kg Gun mass: 169 kg Estimated speed loss: 2 km/h 2 x 50 kg General Purpose Bombs FAB-50sv Additional mass: 120 kg Ammunition mass: 100 kg Racks mass: 20 kg Estimated speed loss before drop: 20 km/h Estimated speed loss after drop: 12 km/h 2 x 104 kg General Purpose Bombs FAB-100M Additional mass: 228 kg Ammunition mass: 208 kg Racks mass: 20 kg Estimated speed loss before drop: 27 km/h Estimated speed loss after drop: 12 km/h 6 x 82mm High Explosive unguided rockets ROS-82 Additional mass: 60 kg Ammunition mass: 42 kg Racks mass: 18 kg Estimated speed loss before launch: 23 km/h Estimated speed loss after launch: 17 km/h Operation features: - Engine has a two-stage mechanical supercharger which must be manually switched at 2500m altitude. - Engine mixture control is manual, it is necessary to lean the mixture if altitude is more than 3-4 km for optimal engine operation. Also, leaning the mixture allows a reduction in fuel consumption during flight. - Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM. - Water and oil radiator shutters is manually controlled. - Airplane has trimmers for all flight-controls: pitch, roll, yaw. - Landing flaps have a hydraulic actuator and they can be extended to any angle up to 60°. - Airplane tail wheel rotates freely and does not have a lock. For this reason, it is necessary to confidently and accurately operate the rudder pedals during the takeoff and landing. - Airplane has differential pneumatic wheel brakes with shared control lever. This means that if the brake lever is held and the rudder pedal the opposite wheel brake is gradually released causing the plane to swing to one side or the other. - Airplane has a fuel gauge which shows total remaining fuel. - Cockpit canopy has a weak lock when in the opened position, for this reason the canopy may spontaneously close in a deep dive. Also, it is impossible to open or close canopy at high speed due to strong airflow. The canopy has no emergency release, so bail out requires the speed drop before it. - The control system of wing-mounted bomb racks only allows the dropping of bombs one by one. - When rockets are installed a salvo controller is used, it has three launch modes: single fire, fire two in a salvo or fire four in a salvo. Yak-1 series 69 Indicated stall speed in flight configuration: 155..171 km/h Indicated stall speed in takeoff/landing configuration: 133..146 km/h Dive speed limit: 720 km/h Maximum load factor: 10.3 G Stall angle of attack in flight configuration: 18 ° Stall angle of attack in landing configuration: 15.6 ° Maximum true air speed at sea level, engine mode - Nominal, 2550 RPM: 514 km/h Maximum true air speed at 2000 m, engine mode - Nominal, 2700 RPM: 549 km/h Maximum true air speed at 4000 m, engine mode - Nominal, 2700 RPM: 582 km/h Service ceiling: 10200 m Climb rate at sea level: 16.9 m/s Climb rate at 3000 m: 15.0 m/s Climb rate at 6000 m: 9.4 m/s Maximum performance turn at sea level: 19.2 s, at 270 km/h IAS. Maximum performance turn at 3000 m: 24.6 s, at 270 km/h IAS. Flight endurance at 3000 m: 1.9 h, at 350 km/h IAS. Takeoff speed: 160..190 km/h Glideslope speed: 195..205 km/h Landing speed: 135..145 km/h Landing angle: 12 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates and turn times are given for Nominal (2700 RPM) power. Engine: Model: M-105PF Maximum power in Nominal mode (2550 RPM) at sea level: 1240 HP Maximum power in Nominal mode (2700 RPM) at sea level: 1210 HP Maximum power in Nominal mode (2700 RPM) at 800 m: 1260 HP Maximum power in Nominal mode (2700 RPM) at 2700 m: 1200 HP Engine modes: Nominal (unlimited time): 2550/2700 RPM, 1050 mm Hg Water rated temperature in engine output: 70..85 °C Water maximum temperature in engine output: 100 °C Oil rated temperature in engine output: 90..100 °C Oil maximum temperature in engine output: 115 °C Supercharger gear shift altitude: 2300 m Empty weight: 2365 kg Minimum weight (no ammo, 10% fuel): 2583 kg Standard weight: 2932 kg Maximum takeoff weight: 3170 kg Fuel load: 304 kg / 408 l Useful load: 805 kg Forward-firing armament: 20mm gun "SsVAK", 120 rounds, 800 rounds per minute, nose-mounted 2 x 7.62mm machine gun "ShKAS", 750 rounds, 1800 rounds per minute, synchronized Bombs: 2 x 50 kg general purpose bombs "FAB-50sv" 2 x 104 kg general purpose bombs "FAB-100M" Rockets: Up to 6 x 7 kg rockets "ROS-82", HE payload mass 2.52 kg Length: 8.5 m Wingspan: 10 m Wing surface: 17.15 m^2 Combat debut: May 1942 Additional airplane configurations list: 2 x 50 kg General Purpose Bombs FAB-50sv Additional mass: 120 kg Ammunition mass: 100 kg Racks mass: 20 kg Estimated speed loss before drop: 20 km/h Estimated speed loss after drop: 12 km/h 2 x 104 kg General Purpose Bombs FAB-100M Additional mass: 228 kg Ammunition mass: 208 kg Racks mass: 20 kg Estimated speed loss before drop: 27 km/h Estimated speed loss after drop: 12 km/h 2 x 82mm High Explosive unguided rockets ROS-82 Additional mass: 60 kg Ammunition mass: 42 kg Racks mass: 18 kg Estimated speed loss before launch: 8 km/h Estimated speed loss after launch: 6 km/h 6 x 82mm High Explosive unguided rockets ROS-82 Additional mass: 60 kg Ammunition mass: 42 kg Racks mass: 18 kg Estimated speed loss before launch: 23 km/h Estimated speed loss after launch: 17 km/h RPK-10 fixed loop radio compass for navigation with radio beacons Additional mass: 10 kg Estimated speed loss: 0 km/h Operation features: - Engine has a two-stage mechanical supercharger which must be manually switched at 2300m altitude. - Engine mixture control is manual; it is necessary to lean the mixture if altitude is more than 3-4 km for optimal engine operation. Also, leaning the mixture allows a reduction in fuel consumption during flight. - Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM. - Water and oil radiator shutter control is manual. - Airplane has only a flight-control trimmer on the pitch. - Landing flaps have a pneumatic actuator. Flaps can only be fully extended; gradual extending is impossible. Due to the weak force of the actuator the extended landing flaps may be pressed upwards by the airflow if the airspeed is more than 220 km/h. Remember that the flaps will not extend fully in case of high speed. In case of a high-speed landing approach the flaps may extend a few steps further right before landing. - Airplane has a manual control for the tailwheel lock. The unlocked tailwheel has a 90° turn limit. The tailwheel should be locked when taxiing straight for a long distance and before takeoff and landing. - Airplane has differential pneumatic wheel brakes with shared control lever. This means that if the brake lever is held and the rudder pedal the opposite wheel brake is gradually released causing the plane to swing to one side or the other. - Fuel gauges are installed on left and right wing fuel tanks, outside of the cockpit. They show remaining fuel level only when there is less than 80 liters of fuel left in the tank. - It is impossible to open or close the canopy at high speed due to strong airflow. The canopy has no emergency release, so bail out requires the speed drop before it. - The control system for the wing-mounted bomb racks only allows releasing of both bombs together. - When rockets are installed a salvo controller can be used, it has three launch modes: single fire, fire two in a salvo or fire four in a salvo. Il-2 model of 1942 Indicated stall speed in flight configuration: 138..158 km/h Indicated stall speed in takeoff/landing configuration: 130..148 km/h Dive speed limit: 570 km/h Maximum load factor: 10.5 G Stall angle of attack in flight configuration: 19.4 ° Stall angle of attack in landing configuration: 17.5 ° Maximum true air speed at sea level, engine mode - Boosted: 400 km/h Maximum true air speed at sea level, engine mode - Nominal: 380 km/h Maximum true air speed at 2500 m, engine mode - Nominal: 414 km/h Service ceiling: 6000 m Climb rate at sea level: 7.1 m/s Climb rate at 3000 m: 5.6 m/s Climb rate at 6000 m:m/s Maximum performance turn at sea level: 25.7 s, at 250 km/h IAS. Maximum performance turn at 3000 m: 37.3 s, at 250 km/h IAS. Flight endurance at 3000 m: 1.7 h, at 300 km/h IAS. Takeoff speed: 150..190 km/h Glideslope speed: 185..195 km/h Landing speed: 135..145 km/h Landing angle: 11.7 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates are given for Nominal power, turn times are given for Boosted power. Engine: Model: AM-38 Maximum power in Boosted mode at sea level: 1600 HP Maximum power in Nominal mode at sea level: 1500 HP Maximum power in Nominal mode at 1650 m: 1500 HP Engine modes: Nominal (unlimited time): 2050 RPM, 1180 mm Hg Boosted power (up to 10 minutes): 2150 RPM, 1280 mm Hg Water rated temperature in engine output: 80..110 °C Water maximum temperature in engine output: 120 °C Oil rated temperature in engine intake: 40..80 °C Oil maximum temperature in engine intake: 85 °C Oil rated temperature in engine output: 115 °C Oil maximum temperature in engine output: 120 °C Supercharger gear shift altitude: single gear Empty weight: 4462 kg Minimum weight (no ammo, 10% fuel): 4651 kg Standard weight: 5294 kg Maximum takeoff weight: 6127 kg Fuel load: 535 kg / 730 l Useful load: 1665 kg Forward-firing armament: 2 x 20mm gun "SsVAK", 250 rounds, 800 rounds per minute, wing-mounted 2 x 7.62mm machine gun "ShKAS", 750 rounds, 1800 rounds per minute, wing-mounted 2 x 23mm gun "VYa-23", 150 rounds, 600 rounds per minute, wing-mounted (modification) 2 x 37mm gun "Sh-37", 40 rounds, 185 rounds per minute, wing-mounted (modification) Defensive armament: Backward: 7.62mm machine gun "ShKAS", 500 rounds, 1800 rounds per minute (modification) Bombs: Up to 6 x 50 kg general purpose bombs "FAB-50sv" Up to 6 x 104 kg general purpose bombs "FAB-100M" 2 x 254 kg general purpose bombs "FAB-250sv" Rockets: 8 x 7 kg rockets "ROS-82", HE payload mass 2.5 kg 8 x 15 kg rockets "RBS-82", HEAT payload mass 7.2 kg 8 x 42 kg rockets "ROFS-132", HE payload mass 21.3 kg Length: 11.5 m Wingspan: 14.6 m Wing surface: 38.5 m^2 Combat debut: June 1942 Additional airplane configurations list: 2 VYa-23 23mm wing-mounted guns with 150 rounds per each Additional mass: 91 kg Ammunition mass: 170 kg Guns mass: 132 kg Estimated speed loss: 1 km/h 2 gun pods with Sh-37 37mm guns with 40 rounds per each Additional mass: 495 kg Ammunition mass: 101 kg Guns mass: 605 kg Estimated speed loss: 19 km/h 2 x 254 kg General Purpose Bombs FAB-250sv Additional mass: 538 kg Ammunition mass: 508 kg Racks mass: 30 kg Estimated speed loss before drop: 18 km/h Estimated speed loss after drop: 7 km/h 8 x 82mm Armour Piercing unguided rockets RBS-82 or 8 x 132mm High Explosive unguided rockets ROFS-132 RBS-82: Additional mass: 144 kg Ammunition mass: 120 kg Racks mass: 24 kg Estimated speed loss before launch: 10 km/h Estimated speed loss after launch: 7 km/h ROFS-132: Additional mass: 376 kg Ammunition mass: 336 kg Racks mass: 40 kg Estimated speed loss before launch: 18 km/h Estimated speed loss after launch: 9 km/h Rear turret with ShKAS 7.62mm machinegun with 500 rounds Additional mass: 130 kg Estimated speed loss: 40 km/h Operation features: - Engine has a boost mode which is engaging by setting mixture control lever to maximum position. - Engine has a single stage mechanical supercharger which does not require manual control. - Engine mixture control is automatic when the mixture lever is set to the intermediate (50%) position. It is possible to manually lean the mixture by moving the control lever to less than 50%. This will lower fuel consumption during flight. - Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM. - Water and oil radiator shutter control is manual. Airplane has armored oil radiator shutters which should to be closed on start of ground attack to reduce possibility of combat damage. After finishing the attack, it is necessary to re-open the shutters to the required position. - Airplane has only the pitch flight-control trimmer. - Landing flaps have a pneumatic actuator. Flaps can only be fully extended; gradual extending is impossible. Due to the weak force of the actuator the extended landing flaps may be pressed upwards by the airflow if the airspeed is more than 220 km/h. Remember that the flaps will not extend fully in case of high speed. In case of a high-speed landing approach the flaps may extend a few steps further right before landing. - Airplane has a manual tail wheel lock. Wheel should be locked when taxiing straight for a long distance and before takeoff and landing. - Airplane has differential pneumatic wheel brakes with shared control lever. This means that if the brake lever is held and the rudder pedal the opposite wheel brake is gradually released causing the plane to swing to one side or the other. - Airplane has a fuel gauge which shows the amount of remaining fuel in the front or bottom fuel tank depending on the switch position. In game the fuel indication switch changes by itself during horizontal flight by every 10 seconds. Rear fuel tank level is not indicated. - Cockpit canopy weight is 50 kg and it has no lock in the open position, for this reason the canopy may to spontaneously close in a deep dive. Also, it is impossible to open or close canopy at high speed due to strong airflow. The canopy has no emergency release, so bail out requires the speed drop before it. - Airplane is equipped with a bomb salvo controller, it has three release modes: single drop, drop two in a salvo or drop four in a salvo. - Airplane is equipped with a rockets salvo controller, it has three launch modes: single fire, fire two in a salvo or fire four in a salvo. - The gunsight is installed on a sliding bar which allows the pilot to extend the gunsight towards the pilot allowing fo an increase in the field of view through the gunsight. Pe-2 series 87 Indicated stall speed in flight configuration: 175..200 km/h Indicated stall speed in takeoff/landing configuration: 148..169 km/h Dive speed limit: 790 km/h Maximum load factor: 11 G Stall angle of attack in flight configuration: 13.9 ° Stall angle of attack in landing configuration: 9.8 ° Maximum true air speed at sea level, engine mode - Nominal: 446 km/h Maximum true air speed at 2000 m, engine mode - Nominal: 476 km/h Maximum true air speed at 5000 m, engine mode - Nominal: 498 km/h Service ceiling: 8000 m Climb rate at sea level: 10.4 m/s Climb rate at 3000 m: 7.8 m/s Climb rate at 6000 m: 3.0 m/s Maximum performance turn at sea level: 29.9 s, at 270 km/h IAS. Maximum performance turn at 3000 m: 40.3 s, at 270 km/h IAS. Flight endurance at 3000 m: 2.8 h, at 300 km/h IAS. Takeoff speed: 160..200 km/h Glideslope speed: 220..240 km/h Landing speed: 155..165 km/h Landing angle: 12.5 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates and turn times are given for Nominal power. Engine: Model: M-105RF Maximum power in Nominal mode at sea level: 1200 HP Maximum power in Nominal mode at 800 m: 1260 HP Maximum power in Nominal mode at 2700 m: 1200 HP Engine modes: Nominal (unlimited time): 2700 RPM, 1050 mm Hg Water rated temperature in engine output: 70..85 °C Water maximum temperature in engine output: 100 °C Oil rated temperature in engine output: 90..100 °C Oil maximum temperature in engine output: 115 °C Supercharger gear shift altitude: 2300 m Empty weight: 6089 kg Minimum weight (no ammo, 10% fuel): 6643 kg Standard weight: 7685 kg Maximum takeoff weight: 8701 kg Fuel load: 1113 kg / 1484 l Useful load: 2612 kg Forward-firing armament: 12.7mm machine gun "UB", 150 rounds, 1000 rounds per minute, nose-mounted 7.62mm machine gun "ShKAS", 450 rounds, 1800 rounds per minute, nose-mounted Defensive armament: Top: 12.7mm machine gun "UB", 200 rounds, 1000 rounds per minute Belly: 12.7mm machine gun "UB", 200 rounds, 1000 rounds per minute Side: 7.62mm machine gun "ShKAS", 225 rounds, 1800 rounds per minute Top turret: 12.7mm machine gun "UB", 200 rounds, 1000 rounds per minute (modification "series 110") Bombs: Up to 10 x 104 kg general purpose bombs "FAB-100M" Up to 4 x 254 kg general purpose bombs "FAB-250sv" Up to 2 x 512 kg general purpose bombs "FAB-500M" Rockets: 10 x 23 kg rockets "ROS-132", HE payload mass 9.1 kg Length: 12.69 m Wingspan: 17.12 m Wing surface: 40.8 m^2 Combat debut: May 1942 Additional airplane configurations list: 10 x 104 kg General Purpose Bombs FAB-100M Additional mass: 1040 kg Ammunition mass: 1040 kg Estimated speed loss before drop: 23 km/h Estimated speed loss after drop: 0 km/h 4 x 254 kg General Purpose Bombs FAB-250sv Additional mass: 1016 kg Ammunition mass: 1016 kg Estimated speed loss before drop: 33 km/h Estimated speed loss after drop: 0 km/h 2 x 512 kg General Purpose Bombs FAB-500M Additional mass: 1024 kg Ammunition mass: 1024 kg Estimated speed loss before drop: 48 km/h Estimated speed loss after drop: 0 km/h 10 x 132mm High Explosive unguided rockets ROS-132 Additional mass: 280 kg Ammunition mass: 230 kg Racks mass: 50 kg Estimated speed loss before launch: 31 km/h Estimated speed loss after launch: 20 km/h VUB-1 rear wide-angle turret with UBT 12.7mm machinegun with 200 rounds Additional mass: 0 kg Estimated speed loss: 5 km/h Operation features: - Engine has a two-stage mechanical supercharger which must be manually switched at 2300m altitude. - Engine mixture control is manual; it is necessary to lean the mixture if altitude is more than 3-4 km for optimal engine operation. Also, leaning the mixture allows a reduction in fuel consumption during flight. - Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM. - Water radiator shutter control is manual. Oil radiator shutters are fixed. - Airplane has trimmers for all flight-controls: pitch, roll, yaw. - Airplane has fence-type airbrakes which are located under the wing and used to slow the descent during steep dive bombing. - Landing flaps have electro-hydraulic actuator and they can be extended to any angle up to 50°. When landing and the flaps are fully extended the angle of attack for a stall is less than landing pitch angle. For this reason, it is prohibited to extend flaps to more than to 35° (70%) on landing. - Airplane has automatically controlled horizontal stabilizer. The automatic control system adjusts the stabilizer angle depending on landing flaps extended angle. - Airplane tail wheel rotates freely and does not have a lock. For this reason, it is necessary to confidently and accurately operate the rudder pedals during the takeoff and landing. - Airplane has differential pneumatic wheel brakes with shared control lever. This means that if the brake lever is held and the rudder pedal the opposite wheel brake is gradually released causing the plane to swing to one side or the other. - Airplane has a fuel gauge which shows total fuel remaining. - Cockpit canopy have an emergency release system for bailouts. - Airplane is equipped with a bomb salvo controller, it has four release modes: drop single, drop two in a salvo, drop four in a salvo or drop all bombs in salvo. There is also a controller for a drop delay between each bomb in the salvo. - When rockets are installed a salvo controller can be used, it has three launch modes: single fire, fire two in a salvo or fire four in a salvo. Aircraft has a fire control system that is designed for eight rockets. However, for added punch, ten rockets were typically loaded. In that case, the ninth rocket will fire with the seventh and the tenth will fire with the eighth. Bf 109 F-4 Indicated stall speed in flight configuration: 154..171 km/h Indicated stall speed in takeoff/landing configuration: 148..161 km/h Dive speed limit: 850 km/h Maximum load factor: 11 G Stall angle of attack in flight configuration: 19.9 ° Stall angle of attack in landing configuration: 17 ° Maximum true air speed at sea level, engine mode - Combat: 522 km/h Maximum true air speed at 2000 m, engine mode - Combat: 570 km/h Maximum true air speed at 6000 m, engine mode - Combat: 635 km/h Service ceiling: 11600 m Climb rate at sea level: 19.5 m/s Climb rate at 3000 m: 18.8 m/s Climb rate at 6000 m: 14.9 m/s Maximum performance turn at sea level: 20.3 s, at 270 km/h IAS. Maximum performance turn at 3000 m: 26.1 s, at 270 km/h IAS. Flight endurance at 3000 m: 2.6 h, at 350 km/h IAS. Takeoff speed: 150..180 km/h Glideslope speed: 190..200 km/h Landing speed: 145..155 km/h Landing angle: 14.8 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates are given for Combat power, turn times are given for Emergency power. Engine: Model: DB-601E Maximum power in Emergency mode at sea level: 1350 HP Maximum power in Emergency mode at 4800 m: 1320 HP Maximum power in Combat mode at sea level: 1200 HP Maximum power in Combat mode at 4900 m: 1200 HP Engine modes: Nominal (unlimited time): 2300 RPM, 1.15 ata Combat power (up to 30 minutes): 2500 RPM, 1.3 ata Emergency power (up to 1 minute): 2700 RPM, 1.42 ata Water rated temperature in engine output: 100..102 °C Water maximum temperature in engine output: 115 °C Oil rated temperature in engine intake: 70..80 °C Oil maximum temperature in engine intake: 85 °C Supercharger gear shift altitude: fluid coupling Empty weight: 2382 kg Minimum weight (no ammo, 10% fuel): 2545 kg Standard weight: 2890 kg Maximum takeoff weight: 3189 kg Fuel load: 304 kg / 400 l Useful load: 807 kg Forward-firing armament: 20mm gun "MG 151/20", 200 rounds, 700 rounds per minute, nose-mounted 2 x 7.92mm machine gun "MG 17", 500 rounds, 1200 rounds per minute, synchronized 2 x 15mm gun "MG 151/15", 135 rounds, 700 rounds per minute, wing-mounted (modification) 2 x 20mm gun "MG 151/20", 135 rounds, 700 rounds per minute, wing-mounted (modification) Bombs: Up to 4 x 55 kg general purpose bombs "SC 50" 249 kg general purpose bomb "SC 250" Length: 8.94 m Wingspan: 9.97 m Wing surface: 16.1 m^2 Combat debut: June 1941 Additional airplane configurations list: MG 151/15 15mm guns in wing-mounted gun pods with 135 rounds per each Additional mass: 193 kg Ammunition mass: 47 kg Guns mass: 146 kg Estimated speed loss: 11 km/h MG 151/20 20mm guns in wing-mounted gun pods with 135 rounds per each Additional mass: 212 kg Ammunition mass: 55 kg Guns mass: 157 kg Estimated speed loss: 12 km/h 4 x 55 kg General Purpose Bombs SC 50 Additional mass: 260 kg Ammunition mass: 220 kg Racks mass: 40 kg Estimated speed loss before drop: 51 km/h Estimated speed loss after drop: 11 km/h 249 kg General Purpose Bomb SC 250 Additional mass: 279 kg Ammunition mass: 249 kg Racks mass: 30 kg Estimated speed loss before drop: 31 km/h Estimated speed loss after drop: 10 km/h Removed pilot armoured headrest for improved field of view Weight savings: 8 kg Estimated speed loss: 0 km/h Additional pilot protection: armoured triplex wind screen Additional mass: 20 kg Estimated speed loss: 1 km/h Operation features: - Airplane has a wide automatization of the engine systems, in fact, to control speed it is only necessary to use the throttle lever. There is no need to manually set engine revolutions and mixture or supercharger gear in normal flight. - In addition to full-automatic mode there is a special manual control mode for the radiator shutters, which can be used in specific situations. - To reduce swinging during taxiing due to prop-wash the propeller pitch control should be switched to manual mode and pitch should be reduced to minimum. - Airplane has no flight-control trimmers. Airplane is equipped with bendable trim tabs that can be set pre-flight by ground personnel. - Airplane has a manually controlled horizontal stabilizer. It should be set to +1° before takeoff and to -4°...-5° before landing. Also, it may be used to trim the flight stick during the flight. In a deep dive the stabilizer should be set so that the pilot must push the flight stick forward to maintain the dive angle. - Airplane has automatic wing slats. They deploy when the high angle of attack increases which makes pre-stall softer. - Airplane has a manual mechanical system for retracting the landing flaps, for this reason it is necessary to extend landing flaps well before final approach. Markers on the left-wing flap indicate how far the flaps are extended. The flaps can be extended to any angle up to 40°. - Airplane has a manual tail wheel lock. Wheel should be locked when taxiing straight for a long distance and before takeoff and landing. - Airplane has independent left and right hydraulic wheel brake controls. To apply either brake push the upper part of the rudder pedal. - Airplane has a fuel gauge which shows total fuel remaining. Also, it has an emergency fuel warning light (80 liters). - The design of the cockpit canopy does not allow it to be opened during flight. The canopy should be closed before takeoff to prevent damage. The canopy has an emergency release system for bailouts. - The control system for the bomb rack only allows for dropping bombs one by one. - The gunsight has a sliding sun-filter. Bf 109 G-2 Indicated stall speed in flight configuration: 158..174 km/h Indicated stall speed in takeoff/landing configuration: 153..164 km/h Dive speed limit: 850 km/h Maximum load factor: 10.5 G Stall angle of attack in flight configuration: 19.8 ° Stall angle of attack in landing configuration: 17 ° Maximum true air speed at sea level, engine mode - Combat: 530 km/h Maximum true air speed at 2000 m, engine mode - Combat: 577 km/h Maximum true air speed at 7000 m, engine mode - Combat: 656 km/h Service ceiling: 12100 m Climb rate at sea level: 21.0 m/s Climb rate at 3000 m: 19.5 m/s Climb rate at 6000 m: 16.5 m/s Maximum performance turn at sea level: 22.2 s, at 270 km/h IAS. Maximum performance turn at 3000 m: 28.3 s, at 270 km/h IAS. Flight endurance at 3000 m: 2.4 h, at 350 km/h IAS. Takeoff speed: 155..180 km/h Glideslope speed: 195..205 km/h Landing speed: 150..155 km/h Landing angle: 14.8 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates and turn times are given for Combat power. Engine: Model: DB-605A Maximum power in Combat mode at sea level: 1310 HP Maximum power in Combat mode at 5800 m: 1250 HP Engine modes: Nominal (unlimited time): 2300 RPM, 1.15 ata Combat power (up to 30 minutes): 2600 RPM, 1.3 ata Water rated temperature in engine output: 100..102 °C Water maximum temperature in engine output: 115 °C Oil rated temperature in engine intake: 70..80 °C Oil maximum temperature in engine intake: 85 °C Supercharger gear shift altitude: fluid coupling Empty weight: 2486 kg Minimum weight (no ammo, 10% fuel): 2649 kg Standard weight: 2994 kg Maximum takeoff weight: 3283 kg Fuel load: 304 kg / 400 l Useful load: 797 kg Forward-firing armament: 20mm gun "MG 151/20", 200 rounds, 700 rounds per minute, nose-mounted 2 x 7.92mm machine gun "MG 17", 500 rounds, 1200 rounds per minute, synchronized 2 x 20mm gun "MG 151/20", 135 rounds, 700 rounds per minute, wing-mounted (modification) Bombs: Up to 4 x 55 kg general purpose bombs "SC 50" 249 kg general purpose bomb "SC 250" Length: 8.94 m Wingspan: 9.97 m Wing surface: 16.1 m^2 Combat debut: May 1942 Additional airplane configurations list: MG 151/20 20mm guns in wing-mounted gun pods with 135 rounds per each Additional mass: 212 kg Ammunition mass: 55 kg Guns mass: 157 kg Estimated speed loss: 12 km/h 4 x 55 kg General Purpose Bombs SC 50 Additional mass: 260 kg Ammunition mass: 220 kg Racks mass: 40 kg Estimated speed loss before drop: 51 km/h Estimated speed loss after drop: 11 km/h 249 kg General Purpose Bomb SC 250 Additional mass: 279 kg Ammunition mass: 249 kg Racks mass: 30 kg Estimated speed loss before drop: 31 km/h Estimated speed loss after drop: 10 km/h Alternative pilot protection: armoured transparent triplex head rest for better visibility Additional mass: 10 kg Estimated speed loss: 0 km/h Removed pilot armoured headrest for improved field of view Weight savings: 8 kg Estimated speed loss: 0 km/h Operation features: - Airplane has a wide automatization of the engine systems, in fact, to control speed it is only necessary to use the throttle lever. There is no need to manually set engine revolutions and mixture or supercharger gear in normal flight. - In addition to full-automatic mode there is a special manual control mode for the radiator shutters, which can be used in specific situations. - To reduce swinging during taxiing due to prop-wash the propeller pitch control should be switched to manual mode and pitch should be reduced to minimum. - Airplane has no flight-control trimmers. Airplane is equipped with bendable trim tabs that can be set pre-flight by ground personnel. - Airplane has a manually controlled horizontal stabilizer. It should be set to +1° before takeoff and to -4°...-5° before landing. Also, it may be used to trim the flight stick during the flight. In a deep dive the stabilizer should be set so that the pilot must push the flight stick forward to maintain the dive angle. - Airplane has automatic wing slats. They deploy when the high angle of attack increases which makes pre-stall softer. - Airplane has a manual mechanical system for retracting the landing flaps, for this reason it is necessary to extend landing flaps well before final approach. Markers on the left-wing flap indicate how far the flaps are extended. The flaps can be extended to any angle up to 40°. - Airplane has a manual tail wheel lock. Wheel should be locked when taxiing straight for a long distance and before takeoff and landing. - Airplane has independent left and right hydraulic wheel brake controls. To apply either brake push the upper part of the rudder pedal. - Airplane has a fuel gauge which shows total fuel remaining. Also, it has an emergency fuel warning light (80 liters). - The design of the cockpit canopy does not allow it to be opened during flight. The canopy should be closed before takeoff to prevent damage. The canopy has an emergency release system for bailouts. - The control system for the bomb rack only allows for dropping bombs one by one. - The gunsight has a sliding sun-filter. Ju 87 D-3 Indicated stall speed in flight configuration: 137..176 km/h Indicated stall speed in takeoff/landing configuration: 123..155 km/h Dive speed limit: 650 km/h Maximum load factor: 9 G Stall angle of attack in flight configuration: 19.9 ° Stall angle of attack in landing configuration: 18 ° Maximum true air speed at sea level, engine mode - Climb: 367 km/h Maximum true air speed at 2000 m, engine mode - Climb: 389 km/h Maximum true air speed at 6000 m, engine mode - Climb: 422 km/h Service ceiling: 7000 m Climb rate at sea level: 8 m/s Climb rate at 3000 m: 7 m/s Climb rate at 6000 m: 2.5 m/s Maximum performance turn at sea level: 22.2 s, at 230 km/h IAS. Maximum performance turn at 3000 m: 31.3 s, at 230 km/h IAS. Flight endurance at 3000 m: 3.4 h, at 300 km/h IAS. Takeoff speed: 140..170 km/h Glideslope speed: 180..195 km/h Landing speed: 125..145 km/h Landing angle: 11 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates are given for Climb power, turn times are given for Take-off power. Engine: Model: Jumo-211J Maximum power in Take-off mode at sea level: 1420 HP Maximum power in Climb mode at sea level: 1190 HP Maximum power in Climb mode at 1500 m: 1260 HP Maximum power in Climb mode at 4900 m: 1180 HP Engine modes: Nominal (unlimited time): 2250 RPM, 1.15 ata Climb power (up to 30 minutes): 2400 RPM, 1.25 ata Take-off power (up to 1 minute): 2600 RPM, 1.42 ata Water rated temperature in engine output: 80 °C Water maximum temperature in engine output: 110 °C Oil rated temperature in engine output: 90 °C Oil maximum temperature in engine output: 105 °C Supercharger gear shift altitude: automatic Empty weight: 3930 kg Minimum weight (no ammo, 10% fuel): 4250 kg Standard weight: 4835 kg Maximum takeoff weight: 6684 kg Fuel load: 626 kg / 840 l Useful load: 2754 kg Forward-firing armament: 2 x 7.92mm machine gun "MG 17", 1000 rounds, 1200 rounds per minute, nose-mounted 12 x 7.92mm machine gun "MG 81", 250 rounds, 1600 rounds per minute, wing-mounted (modification) 2 x 37mm gun "BK 37", 12 rounds, 160 rounds per minute, wing-mounted (modification) Defensive armament: Backward: 2 x 7.92mm machine gun "MG 81", 500 rounds, 1600 rounds per minute Bombs: Up to 4 x 70 kg general purpose bomb "SD 70" Up to 3 x 249 kg general purpose bombs "SC 250" 500 kg general purpose bomb "SC 500" 1090 kg general purpose bomb "SC 1000" 1780 kg general purpose bomb "SC 1800" Length: 11 m Wingspan: 13.8 m Wing surface: 31.9 m^2 Combat debut: March 1942 Additional airplane configurations list: 2 gun pods with 3 twin 7.92mm MG-81Z machineguns and 1500 rounds per each pod Additional mass: 369 kg Ammunition mass: 89 kg Guns mass: 280 kg Estimated speed loss: 31 km/h 2 gun pods with 37mm autocannons 3.7cm BK with 12 rounds per each Additional mass: 793 kg Ammunition mass: 31 kg Guns mass: 840 kg Estimated speed loss: 33 km/h 1780 kg General Purpose Bomb SC 1800 Additional mass: 1780 kg Ammunition mass: 1780 kg Estimated speed loss before drop: 28 km/h Estimated speed loss after drop: 0 km/h Special impeller-actuated siren for demoralizing enemies in dive attacks Additional mass: 9 kg Estimated speed loss: 12 km/h Additional pilot protection: armoured plates on side of cockpit and canopy Additional mass: 60 kg Estimated speed loss: 0 km/h Operation features: - The engine has a two-stage mechanical supercharger with an automatic switch system that switches gears depending altitude and engine revolutions. It can also be manually switched to first gear. - Engine mixture control is automatic. - Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM. - Water and oil radiators shutters control is manual. - Airplane has only the pitch and roll flight-control trimmers. - Airplane has fence-type airbrakes which are located under the wing and used to slow the descent during steep dive bombing. - Airplane has hydraulic-actuated landing flaps with three fixed positions: retracted, takeoff (25°) and landing (40°). Flap indicator lights are located on left panel near the throttle. - Airplane is also equipped with differential ailerons which are lowered in synch with the flaps. - Airplane has a automatically controlled horizontal stabilizer. An automatic control system adjusts the stabilizer angle depending on the extended angle of the landing flaps. The stabilizer control lamps are located near the throttle lever. - Airplane has a manual tail wheel lock. Wheel should be locked when taxiing straight for a long distance and before takeoff and landing. - Airplane has independent left and right hydraulic wheel brake controls. To apply either brake push the upper part of the rudder pedal. - Airplane have a fuel gauge which shows remaining fuel in left and right fuel tanks depending on switch position. In game the fuel indicator switch changes by itself during horizontal flight by every 10 seconds. Also, the airplane has indicator lights for full internal tanks and a low fuel warning light (160 liters) for each tank. - It is impossible to open or close canopy at high speed due to strong airflow. When the canopy is open, it is impossible to use rear gun because it is linked to canopy. The canopy has an emergency release system for bailouts. - Airplane has a window in the cockpit floor which can be opened by the bomb bay door command. - Airplane is equipped with a salvo controller, it allows the pilot to choose which bomb racks to use (central, left and right wing) and to switch the bomb salvo (single drop or all bombs on the rack). - The gunsight has a sliding sun-filter. He 111 H-6 Indicated stall speed in flight configuration: 150..184 km/h Indicated stall speed in takeoff/landing configuration: 123..151 km/h Dive speed limit: 560 km/h Maximum load factor: 4.5 G Stall angle of attack in flight configuration: 20 ° Stall angle of attack in landing configuration: 17 ° Maximum true air speed at sea level, engine mode - Climb: 369 km/h Maximum true air speed at 2000 m, engine mode - Climb: 398 km/h Maximum true air speed at 5000 m, engine mode - Climb: 405 km/h Service ceiling: 6300 m Climb rate at sea level: 4.5 m/s Climb rate at 3000 m: 3.6 m/s Climb rate at 6000 m: 1.8 m/s Maximum performance turn at sea level: 30.8 s, at 250 km/h IAS. Maximum performance turn at 3000 m: 45.2 s, at 250 km/h IAS. Flight endurance at 3000 m: 8.5 h, at 300 km/h IAS. Takeoff speed: 170..210 km/h Glideslope speed: 180..200 km/h Landing speed: 125..150 km/h Landing angle: 9 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates are given for Climb power, turn times are given for Take-off power. Engine: Model: Jumo-211F Maximum power in Take-off mode at sea level: 1420 HP Maximum power in Climb mode at sea level: 1190 HP Maximum power in Climb mode at 1500 m: 1260 HP Maximum power in Climb mode at 4900 m: 1180 HP Engine modes: Nominal (unlimited time): 2250 RPM, 1.15 ata Climb power (up to 30 minutes): 2400 RPM, 1.25 ata Take-off power (up to 1 minute): 2600 RPM, 1.42 ata Water rated temperature in engine output: 80 °C Water maximum temperature in engine output: 110 °C Oil rated temperature in engine output: 90 °C Oil maximum temperature in engine output: 105 °C Supercharger gear shift altitude: automatic Empty weight: 8963 kg Minimum weight (no ammo, 10% fuel): 9946 kg Standard weight: 13727 kg Maximum takeoff weight: 15239 kg Fuel load: 3214 kg / 4285 l Useful load: 6276 kg Defensive armament: Nose: 7.92mm machine gun "MG 15", 600 rounds, 1000 rounds per minute Top: 7.92mm machine gun "MG 15", 1125 rounds, 1000 rounds per minute Belly-backward: 7.92mm machine gun "MG 15", 1200 rounds, 1000 rounds per minute Belly-forward: 7.92mm machine gun "MG 15", 675 rounds, 1000 rounds per minute Left: 7.92mm machine gun "MG 15", 450 rounds, 1000 rounds per minute Right: 7.92mm machine gun "MG 15", 450 rounds, 1000 rounds per minute Nose: 20mm gun "MG FF", 240 rounds, 540 rounds per minute (modification) Belly-forward: 20mm gun "MG FF", 330 rounds, 540 rounds per minute (modification) Bombs: Up to 16 x 55 kg general purpose bombs "SC 50" Up to 4 x 249 kg general purpose bombs "SC 250" 500 kg general purpose bomb "SC 500" Up to 2 x 1090 kg general purpose bombs "SC 1000" Up to 2 x 1780 kg general purpose bombs "SC 1800" 2400 kg general purpose bomb "SC 2500" Length: 16.38 m Wingspan: 22.5 m Wing surface: 79.5 m^2 Combat debut: June 1941 Additional airplane configurations list: 2 x 1090 kg General Purpose Bomb SC 1000 Additional mass: 2180 kg Ammunition mass: 2180 kg Estimated speed loss before drop: 23 km/h Estimated speed loss after drop: 0 km/h 2 x 1780 kg General Purpose Bomb SC 1800 Additional mass: 3560 kg Ammunition mass: 3560 kg Estimated speed loss before drop: 32 km/h Estimated speed loss after drop: 0 km/h 2400 kg General Purpose Bomb SC 2500 Additional mass: 2400 kg Ammunition mass: 2400 kg Estimated speed loss before drop: 17 km/h Estimated speed loss after drop: 0 km/h Nose turret with 20mm MG FF gun with 240 rounds Additional mass: 46 kg Estimated speed loss: 0 km/h Belly forward-looking turret with 20mm MG FF gun with 300 rounds Additional mass: 147 kg Estimated speed loss: 0 km/h Operation features: - Each engine has a two-stage mechanical supercharger with an automatic switch system that switches gears depending altitude and engine revolutions. It can also be manually switched to first gear. - Engine mixture control is automatic. - Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM. - Propellers have a feathering system which should be activated in case of engine damage to reduce drag of the propeller in auto-rotation. - Water and oil radiator shutter controls are manual. The oil radiator control has five fixed positions. - Airplane has trimmers for all flight-controls: pitch, roll and yaw. - Landing flaps have a hydraulic actuator and they can be extended to any angle up to 60°. - Airplane tail wheel rotates freely and does not have a lock. For this reason, it is necessary to confidently and accurately operate the rudder pedals during the takeoff and landing. - Airplane has independent left and right hydraulic wheel brake controls. To apply either brake push the upper part of the rudder pedal. - Airplane has dedicated fuel gauges for left and right fuel tank groups and there is a switch between the internal and external fuel tank group indicator. In game the fuel indicator switch changes by itself during horizontal flight every 10 seconds. Also, there is dedicated fuel gauge for the fuselage fuel tank. Also, the airplane has low fuel warning lights (200 liters) for left and right fuel tank groups. - Airplane is equipped with an automatic bomb salvo controller, it allows you to switch between the bomb racks to be released (internal or external) and to switch between different salvo quantities. There is also a controller for a drop delay between each bomb in the salvo. Airplanes of "Battle of Kuban": Yak-7B series 36 Indicated stall speed in flight configuration: 155..172 km/h Indicated stall speed in takeoff/landing configuration: 139..154 km/h Dive speed limit: 740 km/h Maximum load factor: 11.5 G Stall angle of attack in flight configuration: 20° Stall angle of attack in landing configuration: 19° Maximum true air speed at sea level, engine mode - Nominal, 2700 RPM: 526 km/h Maximum true air speed at 2000 m, engine mode - Nominal, 2700 RPM: 565 km/h Maximum true air speed at 4000 m, engine mode - Nominal, 2700 RPM: 586 km/h Service ceiling: 10660 m Climb rate at sea level: 16.9 m/s Climb rate at 3000 m: 14.3 m/s Climb rate at 6000 m: 8.6 m/s Maximum performance turn at sea level: 19..20 s, at 310 km/h IAS. Maximum performance turn at 3000 m: 24..25 s, at 310 km/h IAS. Flight endurance at 3000 m: 1.9 h, at 350 km/h IAS. Takeoff speed: 170..175 km/h Glideslope speed: 200 km/h Landing speed: 145..165 km/h Landing angle: 11.5° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates and turn times are given for Nominal (2700 RPM) power. Engine: Model: M-105PF Maximum power in Nominal mode (2700 RPM) at sea level: 1210 HP Maximum power in Nominal mode (2700 RPM) at 700 m: 1260 HP Maximum power in Nominal mode (2700 RPM) at 2700 m: 1180 HP Engine modes: Nominal (unlimited time): 2600/2700 RPM, 1050 mm Hg Water rated temperature in engine output: 70..85 °C Water maximum temperature in engine output: 100 °C Oil rated temperature in engine output: 90..100 °C Oil maximum temperature in engine output: 115 °C Supercharger gear shift altitude: 2000 m Empty weight: 2302 kg Minimum weight (no ammo, 10% fuel): 2630 kg Standard weight: 3002 kg Maximum takeoff weight: 3229 kg Fuel load: 305 kg / 420 l Useful load: 927 kg Forward-firing armament: 20mm gun "SsVAK", 120 rounds, 800 rounds per minute, nose-mounted 2 x 12.7 mm machine gun "UBS", 400 rounds, 900 rounds per minute, synchronized Bombs: 2 x 50 kg general purpose bombs "FAB-50sv" 2 x 104 kg general purpose bombs "FAB-100M" Length: 8.5 m Wingspan: 10 m Wing surface: 17.15 m^2 Combat debut: May 1942 Additional airplane configurations list: 2 x 50 kg General Purpose Bombs FAB-50sv Additional mass: 120 kg Ammunition mass: 100 kg Racks mass: 20 kg Estimated speed loss before drop: 20 km/h Estimated speed loss after drop: 12 km/h 2 x 104 kg General Purpose Bombs FAB-100M Additional mass: 228 kg Ammunition mass: 208 kg Racks mass: 20 kg Estimated speed loss before drop: 27 km/h Estimated speed loss after drop: 12 km/h 2 x 82mm High Explosive unguided rockets ROS-82 Additional mass: 60 kg Ammunition mass: 42 kg Racks mass: 18 kg Estimated speed loss before launch: 8 km/h Estimated speed loss after launch: 6 km/h 6 x 82mm High Explosive unguided rockets ROS-82 Additional mass: 60 kg Ammunition mass: 42 kg Racks mass: 18 kg Estimated speed loss before launch: 23 km/h Estimated speed loss after launch: 17 km/h RPK-10 fixed loop radio compass for navigation with radio beacons Additional mass: 10 kg Estimated speed loss: 0 km/h Operation features: - Engine has a two-stage mechanical supercharger which must be manually switched at 2000 m altitude. - Engine mixture control is manual; it is necessary to lean the mixture if altitude is more than 3-4 km for optimal engine operation. Also, leaning the mixture allows a reduction in fuel consumption during flight. - Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM. - Water and oil radiator shutters are controlled manually. - Airplane has only the pitch flight-control trimmer. - Landing flaps have a pneumatic actuator. Flaps can only be fully extended; gradual extending is impossible. Due to the weak force of the actuator the extended landing flaps may be pressed upwards by the airflow if the airspeed is more than 250 km/h. Remember that the flaps will not extend fully in case of high speed. In case of a high-speed landing approach the flaps may extend a few steps further right before landing. - Airplane has a manual control for the tailwheel lock. The unlocked tailwheel has a 90° turn limit. The tailwheel should be locked when taxiing straight for a long distance and before takeoff and landing. - Airplane has differential pneumatic wheel brakes with shared control lever. This means that if the brake lever is held and the rudder pedal the opposite wheel brake is gradually released causing the plane to swing to one side or the other. - Fuel gauges are installed on left and right wing fuel tanks, outside of the cockpit. They show remaining fuel level only when there is less than 130 liters of fuel left in the tank. - It is impossible to open or close the canopy at high speed due to strong airflow. The canopy has no emergency release, so bail out requires the speed drop before it. - The control system for the wing-mounted bomb racks only allows releasing of both bombs together. P-39L-1 Indicated stall speed in flight configuration: 160..172 km/h Indicated stall speed in takeoff/landing configuration: 140..151 km/h Dive speed limit: 841 km/h Maximum load factor: 13.0 G Stall angle of attack in flight configuration: 18.3 ° Stall angle of attack in landing configuration: 16.3 ° Maximum true air speed at sea level, engine mode - Take-off: 539 km/h Maximum true air speed at 2850 m, engine mode - Take-off: 600 km/h Maximum true air speed at 4600 m, engine mode - Military: 596 km/h Service ceiling: 9300 m Climb rate at sea level: 16.7 m/s Climb rate at 3000 m: 13.5 m/s Climb rate at 6000 m: 7.2 m/s Maximum performance turn at sea level: 21.5 s, at 270 km/h IAS. Maximum performance turn at 3000 m: 30.3 s, at 270 km/h IAS. Flight endurance at 3000 m: 1.6 h, at 350 km/h IAS. Takeoff speed: 150..180 km/h Glideslope speed: 180..210 km/h Landing speed: 155..160 km/h Landing angle: 17.0 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates and turn times are given for Take-off power. Engine: Model: V-1710-63 Maximum power in War Emergency power mode at sea level: 1550 HP Maximum power in Take-off mode at sea level: 1325 HP Maximum power in Military mode at 12000 feet: 1150 HP Maximum power in Nominal mode at 10800 feet: 1000 HP Engine modes: Nominal (unlimited time): 2600 RPM, 37.2 inch Hg Military power (up to 15 minutes): 3000 RPM, 42 inch Hg Take-off power (up to 5 minutes): 3000 RPM, 51 inch Hg Maximum Possible power (up to 2 minutes): 3000 RPM, 60 inch Hg Water rated temperature in engine output: 105..115 °C Water maximum temperature in engine output: 125 °C Oil rated temperature in engine intake: 70..85 °C Oil maximum temperature in engine intake: 90 °C Supercharger gear shift altitude: single gear Empty weight: 2929 kg Minimum weight (no ammo, 10% fuel): 3331 kg Standart weight: 3508 kg Maximum takeoff weight: 3868 kg Fuel load: 326,9 kg / 454 l Useful load: 939 kg Forward-firing armament: 37 мм cannon "М4", 30 rounds, 150 rounds per minute, nose-mounted 2 x 12,7мм machine gun "M2.50", 200 rounds, 850 rounds per minute, synchronized 4 x 7,62мм machine gun "M2.30", 300 or 1000 rounds, 1350 rounds per minute, wing-mounted Bombs: 104 kg general purpose bomb "FAB-100M" 254 kg general purpose bomb "FAB-250sv" Length: 9.2 m Wingspan: 10.4 m Wing surface: 29.82 m^2 Combat debut: late 1942 Additional airplane configurations list: Special 37mm Gun Ammo Load Additional loadout variant for M4 37mm gun: armour piercing (AP) (Lend-Leasing of this type of rounds was limited) 1000 rounds per ammo load for wing-mounted .30 machine guns Additional mass: 83 kg Estimated speed loss: 0 km/h Removal of 4 wing-mounted .30 cal machine guns and rear armour plate to reduce total weight Removed mass: 192 kg Removed ammunition mass: 158 kg Removed guns mass: 20 kg Estimated speed gain: 3 km/h 104 kg General Purpose Bomb FAB-100M Additional mass: 114 kg Ammunition mass: 104 kg Rack mass: 10 kg Estimated speed loss before drop: 18 km/h Estimated speed loss after drop: 3 km/h 254 kg General Purpose Bomb FAB-250tsk Additional mass: 264 kg Ammunition mass: 254 kg Rack mass: 10 kg Estimated speed loss before drop: 19 km/h Estimated speed loss after drop: 7 km/h Bendix MN-28Y fixed loop radio compass for navigation with radio beacons Additional mass: 20 kg Estimated speed loss: 2 km/h Operation features: - There is War Emergency power mode. To engage it, move the throttle to max forward position and set the mxiture control to Full Rich (move it 90% forward to engage the Take-Off mode). - Engine has a single stage mechanical supercharger which does not require manual control. - Engine is equipped with an automatic fuel mixture control which maintains optimal mixture if mixture lever is set to Auto Rich (66%) position. To use automatic mixture leaning to reduce fuel consumption during flight it is necessary to set mixture lever to Auto Lean (33%) position. To stop the engine mixture lever should be set to the Cut Off (0%) position. Full Rich positon is used during take-off, in case of emergency or automatic mixture system malfunction. - Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM. Also it is possible to turn off the governor and control propeller pitch manually. - Water and oil temperatures are controlled manually by adjusting the outlet engine radiator shutters. - Airplane has trimmers for all flight-controls: pitch, roll and yaw. - Airplane has electrically-actuated landing flaps and they can be extended to any angle up to 43°. - The nose gear orients by itself, doesn't have brakes and can't be controlled. Its maximum turn angle is 60° left or right. - Airplane has independent left and right hydraulic wheel brake controls. To apply either brake push the upper part of the rudder pedal. - Airplane is equipped with a parking brake system. - Airplane has two fuel gauges which shows the level in each group of fuel tank. - Although there are two cockpit doors equipped with window lifters, usually only the right one is used. They can't be opened during flight, but can be jettisoned to bail out. - Airplane is equipped with mechanical releasing system for a single bomb. - The gunsight has a sliding sun-filter. There is also a back-up mechanical sight which can be used if main sight is damaged. Il-2 model of 1943 Indicated stall speed in flight configuration: 144..159 km/h Indicated stall speed in takeoff/landing configuration: 135..152 km/h Dive speed limit: 570 km/h Maximum load factor: 10.5 G Stall angle of attack in flight configuration: 19.4 ° Stall angle of attack in landing configuration: 17.5 ° Maximum true air speed at sea level, engine mode - Boosted: 407 km/h Maximum true air speed at sea level, engine mode - Nominal: 389 km/h Maximum true air speed at 1200 m, engine mode - Nominal: 400 km/h Service ceiling: 5600 m Climb rate at sea level: 7.5 m/s Climb rate at 3000 m: 4.2 m/s Maximum performance turn at sea level: 26.6 s, at 250 km/h IAS. Maximum performance turn at 3000 m: 39.3 s, at 250 km/h IAS. Flight endurance at 3000 m: 1.4 h, at 300 km/h IAS. Takeoff speed: 160..200 km/h Glideslope speed: 195..205 km/h Landing speed: 145..155 km/h Landing angle: 11.7 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates are given for Nominal power, turn times are given for Boosted power. Engine: Model: AM-38F Maximum power in Boosted mode at sea level: 1720 HP Maximum power in Nominal mode at sea level: 1500 HP Maximum power in Nominal mode at 750 m: 1500 HP Engine modes: Nominal (unlimited time): 2050 RPM, 1200 mm Hg Boosted power (up to 5 minutes): 2350 RPM, 1360 mm Hg Water rated temperature in engine output: 80..110 °C Water maximum temperature in engine output: 120 °C Oil rated temperature in engine intake: 40..80 °C Oil maximum temperature in engine intake: 85 °C Oil rated temperature in engine output: 115 °C Oil maximum temperature in engine output: 120 °C Supercharger gear shift altitude: single gear Empty weight: 4715 kg Minimum weight (no ammo, 10% fuel): 5014 kg Standard weight: 5681 kg Maximum takeoff weight: 6375 kg Fuel load: 535 kg / 730 l Useful load: 1660 kg Forward-firing armament: 2 x 20mm gun "SsVAK", 250 rounds, 800 rounds per minute, wing-mounted 2 x 7.62mm machine gun "ShKAS", 750 rounds, 1800 rounds per minute, wing-mounted 2 x 23mm gun "VYa-23", 150 rounds, 600 rounds per minute, wing-mounted (modification) 2 x 37mm gun "NS-37", 50 rounds, 250 rounds per minute, wing-mounted (modification) Defensive armament: Backward: 12.7 mm machine gun "UBT", 150 rounds, 1000 rounds per minute (modification) Bombs: Up to 240 x 1.5 kg HEAT bomblets "PTAB-2,5-1,5" Up to 6 x 50 kg general purpose bombs "FAB-50sv" Up to 6 x 104 kg general purpose bombs "FAB-100M" 2 x 254 kg general purpose bombs "FAB-250sv" Rockets: 4 x 7 kg rockets "ROS-82", HE payload mass 2.5 kg 4 x 15 kg rockets "RBS-82", HEAT payload mass 7.2 kg 4 x 42 kg rockets "ROFS-132", HE payload mass 21.3 kg Length: 11.5 m Wingspan: 14.6 m Wing surface: 38.5 m^2 Combat debut: early 1943 Additional airplane configurations list: 2 VYa-23 23mm wing-mounted guns with 150 rounds per each Additional mass: 91 kg Ammunition mass: 170 kg Guns mass: 132 kg Estimated speed loss: 1 km/h Two NS-37 37mm gun pods with 50 rounds per each Additional mass: 260 kg Ammunition mass: 90 kg Guns mass: 340 kg Estimated speed loss: 15 km/h 2 x 254 kg General Purpose Bombs FAB-250sv Additional mass: 538 kg Ammunition mass: 508 kg Racks mass: 30 kg Estimated speed loss before drop: 18 km/h Estimated speed loss after drop: 7 km/h 4 x 82mm Armour Piercing unguided rockets RBS-82 or 4 x 132mm High Explosive unguided rockets ROFS-132 RBS-82: Additional mass: 72 kg Ammunition mass: 60 kg Racks mass: 24 kg Estimated speed loss before launch: 5 km/h Estimated speed loss after launch: 4 km/h ROFS-132: Additional mass: 188 kg Ammunition mass: 168 kg Racks mass: 20 kg Estimated speed loss before launch: 9 km/h Estimated speed loss after launch: 5 km/h 192(240) x 1.5 kg HEAT (anti-tank) bomblets PTAB-2.5-1.5 Additional mass: 308(380) kg Ammunition mass: 288(360) kg Racks mass: 20 kg Estimated speed loss before drop: 5 km/h Estimated speed loss after drop: 0 km/h Operation features: - Engine has a boost mode which is engaged by setting mixture control lever to maximum position. - Engine has a single stage mechanical supercharger which does not require manual control. - Engine mixture control is automatic when the mixture lever is set to the intermediate (50%) position. It is possible to manually lean the mixture by moving the control lever to less than 50%. This will lower fuel consumption during flight. - Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM. - Water and oil radiator shutter control is manual. Airplane has armored oil radiator shutters which should be closed at the beginning of ground attack to reduce a possibility of combat damage. After finishing the attack, it is necessary to re-open the shutters to the required position. - Airplane has only the pitch flight-control trimmer. - Landing flaps have a pneumatic actuator. Flaps can be extended fully or to takeoff position - 17°, gradual extending is impossible. Due to the weak force of the actuator the extended landing flaps may be pressed upwards by the airflow if the airspeed is more than 220 km/h. Remember that the flaps will not extend fully in case of high speed. In case of a high-speed landing approach the flaps may extend a few steps further right before the landing which will cause the aircraft to shoot upwards. - Airplane has a manual tail wheel lock. Wheel should be locked when taxiing straight for a long distance and before takeoff and landing. - Airplane has differential pneumatic wheel brakes with shared control lever. This means that if the brake lever is held and the rudder pedal the opposite wheel brake is gradually released causing the plane to swing to one side or the other. - Airplane has a fuel gauge which shows the amount of remaining fuel in the front or bottom fuel tank depending on switch position. In game the fuel indicator switch changes by itself during horizontal flight by every 10 seconds. Rear fuel tank level is not indicated. - Cockpit canopy weight is 50 kg and it has no lock in the open position, for this reason the canopy may to spontaneously close in a deep dive. Also, it is impossible to open or close canopy at high speed due to strong airflow. The canopy has no emergency release, so bail out requires the speed drop before it. - Airplane is equipped with a joint salvo controller both for bombs and rockets, it has three release/fire modes: single launch, launch two in a salvo or launch four in a salvo. - The mechanical gun sight "Visier Vladimirova" allows aiming rockets and guns at ground and air targets and horizontal bombing at certain speeds and altitudes. A-20B Indicated stall speed in flight configuration: 161..193 km/h (100..120 mph) Indicated stall speed in takeoff/landing configuration: 139..166 km/h (86..103 mph) Dive speed limit: 665 km/h (412 mph) Maximum load factor: 6.5 G Stall angle of attack in flight configuration: 19.1 ° Stall angle of attack in landing configuration: 17.1 ° Maximum true air speed at sea level, engine mode - Combat: 505 km/h (314 mph) Maximum true air speed at 1000 m, engine mode - Combat: 524 km/h (326 mph) Maximum true air speed at 5000 m, engine mode - Combat: 544 km/h (338 mph) Maximum true air speed at sea level, engine mode - Nominal: 467 km/h (290 mph) Maximum true air speed at 2000 m, engine mode - Nominal: 500 km/h (311 mph) Maximum true air speed at 5000 m, engine mode - Nominal: 525 km/h (326 mph) Service ceiling: 8700 m (28540 ft) Climb rate at sea level: 10.0 m/s (1969 ft/min) Climb rate at 3000 m: 8.2 m/s (1614 ft/min) Climb rate at 6000 m: 5.0 m/s (984 ft/min) Maximum performance turn at sea level: 24.5 s, at 270 km/h IAS. Maximum performance turn at 3000 m: 34.1 s, at 270 km/h IAS. Flight endurance at 3000 m: 3.4 h, at 350 km/h IAS. Engine mode - Cruise, 1st supercharger stage Takeoff speed: 170..195 km/h (105..120 mph) Glideslope speed: 185..225 km/h (115..140 mph) Landing speed: 150..170 km/h (95..105 mph) Landing angle: 3.4 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for aircraft mass with 8 FAB-100 bombs. Note 4: climb rates and turn times are given for Nominal power. Engine: Model: Wright R-2600-11 Maximum power in Cruise mode at 5500 ft: 810 HP Maximum power in Cruise mode at 12000 ft: 765 HP Maximum power in Nominal mode at 5500 ft: 1350 HP Maximum power in Nominal mode at 12000 ft: 1275 HP Maximum power in Combat mode at sea level: 1600 HP Maximum power in Combat mode at 11500 ft: 1400 HP Engine modes: (boost value is listed for 1st and 2nd supercharger gears) Cruise (unlimited time): 1705 RPM, 27,5 / 30,0 inch Hg, mixture "Auto Lean" Nominal (unlimited time): 2300 RPM, 36,0 / 40,0 inch Hg, mixture "Auto Rich" Combat (5 min limit): 2400 RPM, 43,0 / 41,0 inch Hg, mixture "Auto Rich" Oil rated temperature in engine output: 80..95 °C Oil maximum temperature in engine output: 105 °C Cylinder head rated temperature: 140..240 °C Cylinder head maximum temperature: 260 °C Supercharger gear shift altitude: 2900 m (9500 ft) Empty weight: 6781 kg Minimum weight (no ammo, 10% fuel): 7359 kg Standard weight: 8366 kg Maximum takeoff weight: 10466 kg Fuel load: 1057 kg / 1468 l / 388 gal Useful load: 3665 kg Forward-firing armament: 12.7mm machine gun ANM2 .50, 200 rounds, 850 rounds per minute, nose-mounted Defensive armament: Top: 12.7mm machine gun ANM2 .50, 390 rounds, 850 rounds per minute Belly: 7.92mm machine gun ANM2 .30, 600 rounds, 1150 rounds per minute Bombs: Up to 20 x 104 kg general purpose bombs FAB-100M Up to 4 x 254 kg general purpose bombs FAB-250ck Length: 14.54 m Wingspan: 18.69 m Wing surface: 43.18 m^2 Combat debut: spring 1942 Additional airplane configurations list: 20 x 104 kg General Purpose Bombs FAB-100M Additional mass: 2080 kg Ammunition mass: 2080 kg Estimated speed loss before drop: 39 km/h Estimated speed loss after drop: 16 km/h 4 x 254 kg General Purpose Bombs FAB-250tsk Additional mass: 1016 kg Ammunition mass: 1016 kg Estimated speed loss before drop: 39 km/h Estimated speed loss after drop: 16 km/h Bendix MN-28Y fixed loop radio compass for navigation with radio beacons Additional mass: 20 kg Estimated speed loss: 0 km/h Operation features: - Engine has no manifold pressure automatic governor. For this reason, manifold pressure not only depends on throttle position, but also from RPM and altitude. This requires additional checking of manifold pressure to not cause engine damage. - Engine is equipped with an automatic fuel mixture control which maintains optimal mixture if mixture lever is set to Auto Rich (66%) position. To use automatic mixture leaning to reduce fuel consumption during flight it is necessary to set mixture lever to Auto Lean (33%) position. In the case of mulfunction of the automatic mixture control the mixture lever should be set to Full Rich (100%) position. To stop the engine mixture lever should be set to the Cut Off (0%) position. - Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM. - Oil radiators shutters are joint with engine cowl outlet shutters and manually operated. - Airplane has trimmers for all flight-controls: pitch, roll and yaw. - Landing flaps have a hydraulic actuator and they can be extended to any angle up to 50°. - Airplane has independent left and right hydraulic wheel brake controls. To apply either brake push the upper part of the rudder pedal. - Airplane is equipped with a parking brake system. - Airplane is equipped with a siren that warns a pilot if the throttle is set to low position with landing gear retracted. - Airplane is equipped with upper formation lights. - Engine has a two-stage mechanical supercharger which must be manually switched at 2900m (9500 ft) altitude. - Airplane have a fuel gauge which shows remaining fuel in left and right fuel tanks depending on switch position. In game the fuel indicator switch changes by itself during horizontal flight by every 15 seconds. - The aircraft is equipped with an electromechanical safety system that blocks the hydraulic landing gear actuator while the aircraft is on the ground. - The nose gear orients by itself, doesn't have brakes and can't be controlled. - It is forbidden to open the upper cowl flaps during flight, so they should be closed before taking off. - The upper cowl flaps are controlled simultaneously using a shared hydraulic actuator. - There are white and red signal lamps in the tail: the white one is lit while bomb doors are open and the red one lights up for 5 seconds when bombs are released. - The upper cockpit door can't be opened during flight, but there is an emergency jettison handle. - Airplane is equipped with a bomb salvo controller that has four release modes: drop single, drop two in a salvo, drop four in a salvo or drop all bombs in salvo. There is also a controller for a drop delay between each bomb in the salvo. Bf 109 G-4 Indicated stall speed in flight configuration: 165..175 km/h Indicated stall speed in takeoff/landing configuration: 154..167 km/h Dive speed limit: 850 km/h Maximum load factor: 10.5 G Stall angle of attack in flight configuration: 19.8 ° Stall angle of attack in landing configuration: 17 ° Maximum true air speed at sea level, engine mode - Emergency: 540 km/h Maximum true air speed at sea level, engine mode - Combat: 517 km/h Maximum true air speed at 2000 m, engine mode - Combat: 564 km/h Maximum true air speed at 7000 m, engine mode - Combat: 640 km/h Service ceiling: 11800 m Climb rate at sea level: 20.1 m/s Climb rate at 3000 m: 18.9 m/s Climb rate at 6000 m: 15.4 m/s Maximum performance turn at sea level: 21.2 s, at 270 km/h IAS. Maximum performance turn at 3000 m: 27.2 s, at 270 km/h IAS. Flight endurance at 3000 m: 2.4 h, at 350 km/h IAS. Takeoff speed: 155..180 km/h Glideslope speed: 195..205 km/h Landing speed: 150..155 km/h Landing angle: 13.7 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates and turn times are given for Combat power. Engine: Model: DB-605A Maximum power in Emergency mode at sea level: 1480 HP Maximum power in Emergency mode at 5600 m: 1360 HP Maximum power in Combat mode at sea level: 1310 HP Maximum power in Combat mode at 5800 m: 1250 HP Engine modes: Nominal (unlimited time): 2300 RPM, 1.15 ata Combat power (up to 30 minutes): 2600 RPM, 1.3 ata Emergency power (up to 1 minute): 2800 RPM, 1.42 ata Water rated temperature in engine output: 100..102 °C Water maximum temperature in engine output: 115 °C Oil rated temperature in engine intake: 70..80 °C Oil maximum temperature in engine intake: 85 °C Supercharger gear shift altitude: fluid coupling Empty weight: 2506 kg Minimum weight (no ammo, 10% fuel): 2669 kg Standard weight: 3014 kg Maximum takeoff weight: 3303 kg Fuel load: 304 kg / 400 l Useful load: 797 kg Forward-firing armament: 20mm gun "MG 151/20", 200 rounds, 700 rounds per minute, nose-mounted 2 x 7.92mm machine gun "MG 17", 500 rounds, 1200 rounds per minute, synchronized 2 x 20mm gun "MG 151/20", 135 rounds, 700 rounds per minute, wing-mounted (modification) Bombs: Up to 4 x 55 kg general purpose bombs "SC 50" 249 kg general purpose bomb "SC 250" Length: 8.94 m Wingspan: 9.97 m Wing surface: 16.1 m^2 Combat debut: spring 1943 Additional airplane configurations list: MG 151/20 20mm guns in wing-mounted gun pods with 135 rounds per each Additional mass: 212 kg Ammunition mass: 55 kg Guns mass: 157 kg Estimated speed loss: 12 km/h 4 x 55 kg General Purpose Bombs SC 50 Additional mass: 260 kg Ammunition mass: 220 kg Racks mass: 40 kg Estimated speed loss before drop: 51 km/h Estimated speed loss after drop: 11 km/h 249 kg General Purpose Bomb SC 250 Additional mass: 279 kg Ammunition mass: 249 kg Racks mass: 30 kg Estimated speed loss before drop: 31 km/h Estimated speed loss after drop: 10 km/h Alternative pilot protection: armoured transparent triplex head rest for better visibility Additional mass: 10 kg Estimated speed loss: 0 km/h Removed pilot armoured headrest for improved field of view Weight savings: 8 kg Estimated speed loss: 0 km/h Operation features: - Airplane has a wide automatization of the engine systems, in fact, to control speed it is only necessary to use the throttle lever. There is no need to manually set engine revolutions and mixture or supercharger gear in normal flight. - In addition to full-automatic mode there is a special manual control mode for the radiator shutters, which can be used in specific situations. - To reduce swinging during taxiing due to prop-wash the propeller pitch control should be switched to manual mode and pitch should be reduced to minimum. - Airplane has no flight-control trimmers. Airplane is equipped with bendable trim tabs that can be set pre-flight by ground personnel. - Airplane has a manually controlled horizontal stabilizer. It should be set to +1° before takeoff and to -4°...-5° before landing. Also, it may be used to trim the flight stick during the flight. In a deep dive the stabilizer should be set so that the pilot must push the flight stick forward to maintain the dive angle. - Airplane has automatic wing slats. They deploy when the high angle of attack increases which makes pre-stall softer. - Airplane has a manual mechanical system for retracting the landing flaps, for this reason it is necessary to extend landing flaps well before final approach. Markers on the left-wing flap indicate how far the flaps are extended. The flaps can be extended to any angle up to 40°. - Airplane has a manual tail wheel lock. Wheel should be locked when taxiing straight for a long distance and before takeoff and landing. - Airplane has independent left and right hydraulic wheel brake controls. To apply either brake push the upper part of the rudder pedal. - Airplane has a fuel gauge which shows total fuel remaining. Also, it has an emergency fuel warning light (80 liters). - The design of the cockpit canopy does not allow it to be opened during flight. The canopy should be closed before takeoff to prevent damage. The canopy has an emergency release system for bailouts. - The control system for the bomb rack only allows to drop bombs one by one. - The gunsight has a sliding sun-filter. Fw 190 A-5 Indicated stall speed in flight configuration: 169..195 km/h Indicated stall speed in takeoff/landing configuration: 160..175 km/h Dive speed limit: 850 km/h Maximum load factor: 11 G Stall angle of attack in flight configuration: 19.5° Stall angle of attack in landing configuration: 18.1° Maximum true air speed at sea level, engine mode - Emergency: 558 km/h Maximum true air speed at 3000 m, engine mode - Emergency: 578 km/h Maximum true air speed at 6400 m, engine mode - Emergency: 658 km/h Maximum true air speed at sea level, engine mode - Combat: 533 km/h Maximum true air speed at 3000 m, engine mode - Combat: 558 km/h Maximum true air speed at 6000 m, engine mode - Combat: 622 km/h Service ceiling: 10600 m Climb rate at sea level: 15.4 m/s Climb rate at 3000 m: 11.9 m/s Climb rate at 6000 m: 9.7 m/s Maximum performance turn at sea level: 23.5 s, at 280 km/h IAS. Maximum performance turn at 3000 m: 35.5 s, at 280 km/h IAS. Flight endurance at 3000 m: 3.0 h, at 350 km/h IAS. Takeoff speed: 170..210 km/h Glideslope speed: 205..215 km/h Landing speed: 160..170 km/h Landing angle: 12.5° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates are given for Combat power, turn times are given for Emergency power. Engine: Model: BMW-801D Maximum power in Emergency mode at sea level: 1700 HP Maximum power in Emergency mode at 5700 m: 1440 HP Maximum power in Combat mode at 700 m: 1520 HP Maximum power in Combat mode at 5300 m: 1320 HP Engine modes: Nominal (unlimited time): 2300 RPM, 1.2 ata Combat power (up to 30 minutes): 2400 RPM, 1.32 ata Emergency power (up to 3 minutes): 2700 RPM, 1.42 ata Oil rated temperature in engine intake: 60..70 °C Oil maximum temperature in engine intake: 85 °C Oil rated temperature in engine output: 105 °C Oil maximum temperature in engine output: 120 °C Cylinder head rated temperature: 180 °C Cylinder head maximum temperature: 220 °C Supercharger gear shift altitude: automatic Empty weight: 3219 kg Minimum weight (no ammo, 10% fuel): 3401 kg Standard weight: 3926 kg Maximum takeoff weight: 4648 kg Fuel load: 409 kg / 524 l Useful load: 1429 kg Forward-firing armament: 2 x 20mm gun "MG 151/20", 250 rounds, 700 rounds per minute, synchronized 2 x 7.92mm machine gun "MG 17", 900 rounds, 1200 rounds per minute, synchronized 2 x 20mm gun "MG FF", 90 rounds, 540 rounds per minute, wing-mounted (modification) 4 x 20mm gun "MG 151/20", 500 rounds, 700 rounds per minute, wing-mounted (modification) Bombs: Up to 8 x 55 kg general purpose bombs "SC 50" 249 kg general purpose bomb "SC 250" 500 kg general purpose bomb "SC 500" Length: 8.85 m Wingspan: 10.51 m Wing surface: 18.3 m^2 Combat debut: Spring of 1943 Additional airplane configurations list: MG 151/20 20mm guns in wing-mounted gun pods with 125 rounds per each Additional mass: 247 kg Ammunition mass: 105 kg Guns mass: 142 kg Estimated speed loss: 39 km/h MG FF/M 20mm additional wing-mounted guns with 90 rounds per each Additional mass: 131 kg Ammunition mass: 37 kg Guns mass: 94 kg Estimated speed loss: 6 km/h Fw 190 A5/U17 strike modification includes 1.65 ATA modified engine, additional fuselage bottom and engine armor and SC 50 underwing bomb holders Additional mass: 218 kg Estimated speed loss: 14 km/h (with C3 system disengaged) 4 x 55 kg General Purpose Bombs SC 50 Additional mass: 282 kg Ammunition mass: 222 kg Racks mass: 60 kg Estimated speed loss before drop: 83 km/h Estimated speed loss after drop: 39 km/h 249 kg General Purpose Bomb SC 250 Additional mass: 279 kg Ammunition mass: 249 kg Racks mass: 30 kg Estimated speed loss before drop: 37 km/h Estimated speed loss after drop: 13 km/h 500 kg General Purpose Bomb SC 500 Additional mass: 530 kg Ammunition mass: 500 kg Racks mass: 30 kg Estimated speed loss before drop: 41 km/h Estimated speed loss after drop: 13 km/h Operation features: - Airplane has a wide automatization of the engine systems, in fact, to control speed it is only necessary to use the throttle lever. There is no need to manually set engine revolutions and mixture or supercharger gear in normal flight. The engine supercharger has an automatic switch system which depends on altitude and engine revolutions. - U17 strike modification includes C3 additional fuel injection system. When engaged, it increases pressure to 1.65 ATA (10 minutes time limit). This system can be turned on by engine boost command only at 100% throttle, with automatic propeller pitch control enabled and at altitudes lower than 1 km. - Outlet cowl shutters are operated manually. - To reduce swinging during taxiing due to prop-wash the propeller pitch control should be switched to manual mode and pitch should be reduced to minimum. - When the angle of attack increases to critical levels the wing may stall suddenly and unexpectedly. There is almost no pre-stall buffet before the stalling. To avoid this the pilot must pay additional attention when performing extreme maneuvering. - Airplane has no flight-control trimmers. Airplane is equipped with bendable trim tabs that can be set pre-flight by ground personnel. - Airplane has a manually controlled horizontal stabilizer which is electrically-actuated. It should be set to +1.5° before takeoff and landing. Also, it may be used to trim the flight stick during the flight. In a deep dive the stabilizer should be set so that the pilot must push the flight stick forward to maintain the dive angle. - Airplane has electrically-actuated landing flaps with three fixed positions: retracted, takeoff (13°) and landing (58°). Flaps control buttons and indicator lights are located on left panel near the throttle. The flap angle may also be checked by indicators on the left and right wing outside the cockpit. - Airplane has a tail wheel lock system which locks the tail wheel if the flight-stick is pulled backward. The tailwheel should be locked when taxiing straight for a long distance, before takeoff and after touchdown upon landing. - Airplane has independent left and right hydraulic wheel brake controls. To apply either brake push the upper part of the rudder pedal. - Airplane has a fuel gauge which shows the amount of remaining fuel in the front or rear fuel tank depending on switch position. In game the fuel indicator switch changes by itself during horizontal flight by every 10 seconds. Also, the airplane has an emergency fuel warning light (100 liters). - It is impossible to open or close the canopy at high speed due to strong airflow. The canopy has an emergency release system for bailouts. - The control system for the bomb rack only allows for dropping bombs one by one. - The gunsight has a sliding sun-filter. Bf 110 G-2 Indicated stall speed in flight configuration: 160..190 km/h Indicated stall speed in takeoff/landing configuration: 141..168 km/h Dive speed limit: 740 km/h Maximum load factor: 11 G Stall angle of attack in flight configuration: 20.3 ° Stall angle of attack in landing configuration: 17.4 ° Maximum true air speed at sea level, engine mode - Combat: 489 km/h Maximum true air speed at 2000 m, engine mode - Combat: 533 km/h Maximum true air speed at 6500 m, engine mode - Combat: 581 km/h Service ceiling: 10800 m Climb rate at sea level: 15.6 m/s Climb rate at 3000 m: 14.1 m/s Climb rate at 6000 m: 10.7 m/s Maximum performance turn at sea level: 23.5 s, at 270 km/h IAS. Maximum performance turn at 3000 m: 31.2 s, at 270 km/h IAS. Flight endurance at 3000 m: 4.0 h, at 300 km/h IAS. Takeoff speed: 190..230 km/h Glideslope speed: 210..230 km/h Landing speed: 150..170 km/h Landing angle: 10.7 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates are given for Combat power, turn times are given for Emergency power. Engine: Model: DB-605B Maximum power in Emergency mode at sea level: 1480 HP Maximum power in Emergency mode at 5600 m: 1360 HP Maximum power in Combat mode at sea level: 1310 HP Maximum power in Combat mode at 5800 m: 1250 HP Engine modes: Nominal (unlimited time): 2300 RPM, 1.15 ata Combat power (up to 30 minutes): 2600 RPM, 1.3 ata Emergency power (up to 1 minute): 2800 RPM, 1.42 ata Water rated temperature in engine output: 100..102 °C Water maximum temperature in engine output: 115 °C Oil rated temperature in engine intake: 70..80 °C Oil maximum temperature in engine intake: 85 °C Supercharger gear shift altitude: fluid coupling Empty weight: 5905 kg Minimum weight (no ammo, 10% fuel): 6335 kg Standart weight: 7514 kg Maximum takeoff weight: 8928 kg Fuel load: 1003 kg / 1270 l Useful load: 3023 kg Forward-firing armament: 4 x 7.92mm machine gun "MG 17", 1000 rounds, 1200 rounds per minute, nose-mounted 20mm gun "MG 151/20", 400 rounds, 700 rounds per minute, nose-mounted left 20mm gun "MG 151/20", 350 rounds, 700 rounds per minute, nose-mounted right 2 х 20mm gun "MG 151/20", 200 rounds, 700 rounds per minute, nose-mounted (modification) 37mm gun "BK37", 66 rounds, 160 rounds per minute, nose-mounted (modification) Defensive armament: Backward: 2 x 7.92mm machine guns "MG 81", 750 rounds, 1600 rounds per minute Bombs: Up to 12 x 55 kg general purpose bombs "SC 50" Up to 2 x 249 kg general purpose bombs "SC 250" Up to 2 x 500 kg general purpose bombs "SC 500" 1090 kg general purpose bomb "SC 1000" Length: 12.1 m Wingspan: 16.3 m Wing surface: 38.4 m^2 Combat debut: Autumn 1942 Additional airplane configurations list: Removed pilot armoured headrest for improved field of view Removed mass: 8 kg Estimated speed gain: 0 km/h 12 x 55 kg General Purpose Bombs SC 50 Additional mass: 820 kg Ammunition mass: 660 kg Racks mass: 160 kg Estimated speed loss before drop: 80 km/h Estimated speed loss after drop: 38 km/h 2 x 500 kg General Purpose Bomb SC 500 Additional mass: 1025 kg Ammunition mass: 1000 kg Racks mass: 50 kg Estimated speed loss before drop: 35 km/h Estimated speed loss after drop: 5 km/h 1090 kg General Purpose Bomb SC 1000 Additional mass: 1140 kg Ammunition mass: 1090 kg Racks mass: 50 kg Estimated speed loss before drop: 33 km/h Estimated speed loss after drop: 5 km/h Two MG 151/20 20mm guns in fuselage mounted gun pod with 200 rounds per each Additional mass: 274 kg Ammunition mass: 84 kg Guns mass: 190 kg Estimated speed loss: 40 km/h 37mm 3.7cm BK autocannon gun pod with 66 rounds (11 clips with 6 rounds in each) Additional mass: 251 kg Ammunition mass: 95 kg Guns mass: 419 kg Estimated speed loss: 54 km/h Operation features: - Airplane has a wide automatization of the engine systems, in fact, to control speed it is only necessary to use the throttle lever. There is no need to manually set engine revolutions and mixture or supercharger gear in normal flight. - Water and oil radiator shutters are controlled manually. The oil radiator control has five fixed positions. The water radiator control has nine fixed positions. - Propellers have a feathering system which should be activated in case of engine damage to reduce drag of the propeller in auto-rotation. - To reduce swinging during taxiing due to prop-wash it is necessary to use asymmetrical engines thrust. It is recommended to give the left engine 20% more power. Also, the propeller pitch control should be switched to manual mode and pitch should be reduced to minimum. - Airplane has only pitch and yaw flight-control trimmers. - Airplane has automatic wing slats. They deploy when the high angle of attack increases which makes pre-stall softer. - Landing flaps have a hydraulic actuator and they can be extended to any angle up to 50°. - Airplane has an automatically controlled horizontal stabilizer. An automatic control system adjusts the stabilizer angle depending on the extended angle of the landing flaps. - Airplane tail wheel rotates freely and does not have a lock. For this reason, it is necessary to confidently and accurately operate the rudder pedals during the takeoff and landing. - Airplane has independent left and right hydraulic wheel brake controls. To apply either brake push the upper part of the rudder pedal. - Airplane has a fuel gauge which shows the remaining fuel in one of four fuel tanks depending on the switch position. In the game the fuel indicator switch changes by itself during horizontal flight by every 10 seconds. Also, the airplane has a low fuel warning light (50 liters) for each tank. - The design of the cockpit canopy does not allow it to be opened during flight. The canopy should be closed before takeoff to prevent damage. The canopy has an emergency release system for bailouts. - Airplane is equipped with an automatic bomb salvo controller, it allows you to choose which bomb-racks to be released (central belly, left and right wing) and to switch the bomb salvo (single release or release all bombs). - Reloading of BK37 gun is performed by the rear gunner at the pilot`s command. - The gunsight has a sliding sun-filter. He 111 H-16 Indicated stall speed in flight configuration: 150..194 km/h Indicated stall speed in takeoff/landing configuration: 123..156 km/h Dive speed limit: 560 km/h Maximum load factor: 4.5 G Stall angle of attack in flight configuration: 20 ° Stall angle of attack in landing configuration: 17 ° Maximum true air speed at sea level, engine mode - Climb: 370 km/h Maximum true air speed at 2000 m, engine mode - Climb: 399 km/h Maximum true air speed at 5000 m, engine mode - Climb: 410 km/h Service ceiling: 6850 m Climb rate at sea level: 5.3 m/s Climb rate at 3000 m: 4.1 m/s Climb rate at 6000 m: 2.3 m/s Maximum performance turn at sea level: 30.8 s, at 250 km/h IAS. Maximum performance turn at 3000 m: 45.2 s, at 250 km/h IAS. Flight endurance at 3000 m: 6.7 h, at 300 km/h IAS. Takeoff speed: 170..210 km/h Glideslope speed: 180..200 km/h Landing speed: 125..150 km/h Landing angle: 9 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates are given for Climb power, turn times are given for Take-off power. Engine: Model: Jumo-211F Maximum power in Take-off mode at sea level: 1340 HP Maximum power in Climb mode at sea level: 1120 HP Maximum power in Climb mode at 1900 m: 1210 HP Maximum power in Climb mode at 5300 m: 1060 HP Engine modes: Nominal (unlimited time): 2250 RPM, 1.15 ata Climb power (up to 30 minutes): 2400 RPM, 1.25 ata Take-off power (up to 1 minute): 2600 RPM, 1.40 ata Water rated temperature in engine output: 80 °C Water maximum temperature in engine output: 110 °C Oil rated temperature in engine output: 90 °C Oil maximum temperature in engine output: 105 °C Supercharger gear shift altitude: automatic Empty weight: 8698 kg Minimum weight (no ammo, 10% fuel): 9831 kg Standard weight: 13017 kg Maximum takeoff weight: 15689 kg Fuel load: 2553 kg / 3450 l Useful load: 6991 kg Defensive armament: Nose: 20mm gun "MG FF", 240 rounds, 540 rounds per minute Top: 13mm machine gun "MG 131", 1000 rounds, 900 rounds per minute Belly-backward: 2 x 7.92mm machine guns "MG 81", 850 rounds, 1600 rounds per minute Left: 7.92mm machine gun "MG 81", 500 rounds, 1600 rounds per minute Right: 7.92mm machine gun "MG 81", 500 rounds, 1600 rounds per minute Bombs: Up to 16 x 55 kg general purpose bombs "SC 50" Up to 4 x 249 kg general purpose bombs "SC 250" Up to 2 x 500 kg general purpose bombs "SC 500" Up to 2 x 1090 kg general purpose bombs "SC 1000" Up to 2 x 1780 kg general purpose bombs "SC 1800" 2400 kg general purpose bomb "SC 2500" Length: 16.38 m Wingspan: 22.5 m Wing surface: 79.5 m^2 Combat debut: Winter of 1943 Additional airplane configurations list: 2 x 1090 kg General Purpose Bomb SC 1000 Additional mass: 2180 kg Ammunition mass: 2180 kg Estimated speed loss before drop: 23 km/h Estimated speed loss after drop: 0 km/h 2 x 1780 kg General Purpose Bomb SC 1800 Additional mass: 3560 kg Ammunition mass: 3560 kg Estimated speed loss before drop: 32 km/h Estimated speed loss after drop: 0 km/h 2400 kg General Purpose Bomb SC 2500 Additional mass: 2400 kg Ammunition mass: 2400 kg Estimated speed loss before drop: 17 km/h Estimated speed loss after drop: 0 km/h Operation features: - Each engine has a two-stage mechanical supercharger with an automatic switch system that switches gears depending altitude and engine revolutions. It can also be manually switched to first gear. - Engine mixture control is automatic. - Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM. - Propellers have a feathering system which should be activated in case of engine damage to reduce drag of the propeller in auto-rotation. - Water and oil radiator shutter controls are manual. The oil radiator control has five fixed positions. - Airplane has trimmers for all flight-controls: pitch, roll and yaw. - Landing flaps have a hydraulic actuator and they can be extended to any angle up to 60°. - Airplane tail wheel rotates freely and does not have a lock. For this reason, it is necessary to confidently and accurately operate the rudder pedals during the takeoff and landing. - Airplane has independent left and right hydraulic wheel brake controls. To apply either brake push the upper part of the rudder pedal. - Airplane has dedicated fuel gauges for left and right fuel tank groups and there is a switch between the internal and external fuel tank group indicator. In game the fuel indicator switch changes by itself during horizontal flight every 10 seconds. Also, the airplane has low fuel warning lights (200 liters) for left and right fuel tank groups. - Airplane is equipped with an automatic bomb salvo controller, it allows you to switch between the bomb racks to be released (internal or external) and to switch between different salvo quantities. There is also a controller for a drop delay between each bomb in the salvo. Airplanes of "Operation Bodenplatte": Spitfire Mk.IXe Скрытый текст Indicated stall speed in flight configuration: 143...163 km/h Indicated stall speed in takeoff/landing configuration: 135...154 km/h Dive speed limit: 725 km/h Maximum load factor: 12.5 G Stall angle of attack in flight configuration: 18.8 ° Stall angle of attack in landing configuration: 16.0 ° Merlin 66 engine: Maximum true air speed at sea level, 3000 RPM, boost +18: 542 km/h Maximum true air speed at 3350 m, 3000 RPM, boost +18: 610 km/h Maximum true air speed at 6850 m, 3000 RPM, boost +18: 664 km/h Service ceiling: 12500 m Climb rate at sea level: 21.5 m/s Climb rate at 3000 m: 18.6 m/s Climb rate at 6000 m: 15.5 m/s Maximum performance turn at sea level: 17.7 s, at 270 km/h IAS. Maximum performance turn at 3000 m: 20.5 s, at 260 km/h IAS. Merlin 70 engine: Maximum true air speed at sea level, 3000 RPM, boost +18: 532 km/h Maximum true air speed at 4900 m, 3000 RPM, boost +18: 634 km/h Maximum true air speed at 8500 m, 3000 RPM, boost +18: 677 km/h Service ceiling: 13000 m Climb rate at sea level: 18.5 m/s Climb rate at 3000 m: 17.5 m/s Climb rate at 6000 m: 14.1 m/s Maximum performance turn at sea level: 17.8 s, at 270 km/h IAS. Maximum performance turn at 3000 m: 20.7 s, at 260 km/h IAS. Flight endurance at 3000 m: 1 h 40 m, at 350 km/h IAS. Takeoff speed: 185..195 km/h Glideslope speed: 165..185 km/h Landing speed: 150..155 km/h Landing angle: 12.5 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates are given for 2850 RPM and boost +12, turn times are given for 3000 RPM and boost +18. Engine: Model: Merlin 66 Maximum power in Take-off mode (3000 RPM, boost +12, low gear) at sea level: 1320 HP Maximum power in International power mode (2850 RPM, boost +12, low gear) at 9250 feet: 1400 HP Maximum power in International power mode (2850 RPM, boost +12, high gear) at 19000 feet: 1310 HP Maximum power in Emergency Max All Out mode (3000 RPM, boost +18, low gear) at 5750 feet: 1705 HP Maximum power in Emergency Max All Out mode (3000 RPM, boost +18, high gear) at 16000 feet: 1580 HP Model: Merlin 70 Maximum power in Take-off mode (3000 RPM, boost +12, low gear) at sea level: 1250 HP Maximum power in International power mode (2850 RPM, boost +12, low gear) at 13500 feet: 1375 HP Maximum power in International power mode (2850 RPM, boost +12, high gear) at 25250 feet: 1255 HP Maximum power in Emergency Max All Out mode (3000 RPM, boost +18, low gear) at 10000 feet: 1655 HP Maximum power in Emergency Max All Out mode (3000 RPM, boost +18, high gear) at 22250 feet: 1475 HP Engine modes: Max Cruising power (unlimited time): 2650 RPM, boost +7 International power (up to 1 hour): 2850 RPM, boost +12 Emergency Max All Out power (up to 5 minutes): 3000 RPM, boost +18 Water rated temperature in engine output: 105..115 °C Water maximum temperature in engine output: 135 °C Oil rated temperature in engine intake: 90 °C Oil maximum temperature in engine intake: 105 °C Supercharger gear shift altitude: automatic with possibility of manual switch to low gear Empty weight: 2530 kg Minimum weight (no ammo, 10% fuel): 2977 kg Standard weight: 3359 kg Fuel load: 274 kg / 386 l / 85 gallons Maximum useful load: 1302 kg Forward-firing armament: 2 x 20mm gun "Hispano Mk.II", 120 rounds per gun, 650 rounds per minute, wing-mounted 2 x 12.7mm machine gun "Browning .50", 250 rounds per gun, 850 rounds per minute, wing-mounted Bombs: 2 x 250 lb general purpose bomb "250 lb. G.P." 500 lb general purpose bomb "500 lb. G.P." Rockets: 2 x 25 lb armour-piercing rocket "RP-3 A.P. 25 lb. mk.II" 2 x 60 lb semi-armour-piercing rocket "RP-3 S.A.P. 60 lb. mk.II" Length: 9.65 m Wingspan: 11.21 m Wing surface: 22.48 m^2 Combat debut: June 1942 Additional airplane configurations list: Скрытый текст 500 lb General Purpose Bomb Additional mass: 237 kg Ammunition mass: 227 kg Racks mass: 10 kg Estimated speed loss before drop: 13 km/h Estimated speed loss after drop: 7 km/h 2 x 250 lb General Purpose Bombs Additional mass: 247 kg Ammunition mass: 227 kg Racks mass: 20 kg Estimated speed loss before drop: 24 km/h Estimated speed loss after drop: 8 km/h 2 х 82-in High Explosive or Armour Piercing unguided rockets RP-3RP-3 HE: Additional mass: 106 kg Ammunition mass: 86 kg Racks mass: 20 kg Estimated speed loss before launch: 23 km/h Estimated speed loss after launch: 17 km/hRP-3 AP: Additional mass: 75 kg Ammunition mass: 55 kg Racks mass: 20 kg Estimated speed loss before launch: 21 km/h Estimated speed loss after launch: 17 km/h MkII Gyro Gunsight Additional mass: 5.2 kg Estimated speed loss: 0 km/h Rear view mirror Additional mass: 1 kg Estimated speed loss: 1 km/h Clipped Wing Removed mass: 4 kg Estimated speed loss: 0 km/h Merlin 70 engine Additional mass: 0 kg Estimated speed loss: 0 km/h 150 grade fuel Allows +25 lb boost Supercharger gear shift automat is disabled. Stages should be manually switched at 9000ft altitude. Estimated speed increase at sea level: 29 km/h Operation features: - Engine is equipped with the automatic governor of the manifold pressure that works when the throttle is set to 1/3 position or above. - Engine has a two stage mechanical supercharger which does not require manual control. It can be switched to the low gear manually. - Engine is equipped with an automatic fuel mixture control which maintains optimal mixture if mixture lever is set to the forward position. It is possible to manually lean the mixture by moving the mixture control to less than maximum. This also reduces fuel consumption during flight. - Engine RPM has an automatic governor that controls the propeller pitch to maintain the required RPM. - The water and oil radiators shutters are operated automatically, but there is a special manual mode that forces radiator shutters to open completely. - Aircraft has a neutral static stability. The elevator effectiveness is high, so the aircraft should be controlled carefully, not giving too much flight stick input. - Aircraft becomes unstable with extended landing flaps. - Aircraft is equipped with elevator and rudder trimmers. - Landing flaps have a pneumatic actuator so they can be extended to maximum position only. Speed with extended landing flaps is limited to 140 mph. - Airplane tail wheel rotates freely and does not have a lock. Since the landing gear wheels are relatively close to each other, it is necessary to confidently and accurately operate the rudder pedals during the takeoff and landing. - Airplane has differential pneumatic wheel brakes with shared control lever. This means that if the brake lever is held and the rudder pedal the opposite wheel brake is gradually released causing the plane to swing to one side or the other. - Airplane is equipped with a siren that warns a pilot if the throttle is set to low position with landing gear retracted. - It is impossible to open or close the canopy at high speed due to strong airflow. The canopy has an emergency release system for bailouts. - The aircraft is equipped with a bottom formation light. - Standard gunsight is adjustable: both the target distance and target base can be set. - The gyroscopic gunsight automaticly calculates required angular deflection while firing at a target. It has 4 modes: fixed reticle, fixed and gyro reticle, gyro reticle, gyro reticle with the target range fixed at 150 yards (night mode). The angular deflection will be calculated correctly only if the target range is set properly. To set the range, adjust the target base first using separate controls and then set the range by adjusting the size of the rangefiding reticle to be the same as the target size. - Both gunsights have sliding sun-filters. Tempest Mk.V ser.2 Indicated stall speed in flight configuration: 150...174 km/h Indicated stall speed in takeoff/landing configuration: 128...149 km/h Dive speed limit: 870 km/h Maximum load factor: 12.0 G Stall angle of attack in flight configuration: 17.5 ° Stall angle of attack in landing configuration: 13.7 ° Maximum true air speed at sea level, 3700 RPM, boost +9: 600 km/h Maximum true air speed at 1950 m, 3700 RPM, boost +9: 664 km/h Maximum true air speed at 5640 m, 3700 RPM, boost +9: 703 km/h Service ceiling: 10800 m Climb rate at sea level: 21.0 m/s Climb rate at 3000 m: 15.1 m/s Climb rate at 6000 m: 12.1 m/s Maximum performance turn at sea level: 20.0 s, at 270 km/h IAS. Maximum performance turn at 3000 m: 27.8 s, at 270 km/h IAS. Flight endurance at 3000 m: 3 h 18 m, at 350 km/h IAS. Takeoff speed: 150...170 km/h Glideslope speed: 170...200 km/h Landing speed: 150..155 km/h Landing angle: 11.6 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates and turn times are given for 3700 RPM and boost +9. Engine: Model: Napier Sabre IIA Maximum power in Combat mode (3700 RPM, boost +9, low gear) at sea level: 2180 HP Maximum power in Combat mode (3700 RPM, boost +9, high gear) at 11500 feet: 1830 HP Engine modes: Max Cruising power (unlimited time): 3150 RPM, boost +4.5 Climb power (up to 1 hour): 3700 RPM, boost +7 Combat power (up to 5 minutes): 3700 RPM, boost +9 Water rated temperature in engine output: 65..125 °C Water maximum temperature in engine output: 130 °C Oil rated temperature in engine intake: 60..90 °C Oil maximum temperature in engine intake: 95 °C Supercharger gear shift altitude: 9500 feet Empty weight: 4354 kg Minimum weight (no ammo, 10% fuel): 4585 kg Standard weight: 5221 kg Maximum takeoff weight: 6190 kg Fuel load: 516 kg / 718 l / 158 gallons Maximum useful load: 1836 kg Forward-firing armament: 4 x 20mm gun "Hispano Mk.V", 150 rounds per gun, 650 rounds per minute, wing-mounted Bombs: 2 x 500 lb general purpose bomb "500 lb. M.C." 2 x 1000 lb general purpose bomb "1000 lb. M.C." Length: 10.26 m Wingspan: 12.50 m Wing surface: 27.81 m² Combat debut: May 1944 Additional airplane configurations list: 2 x 500 lb Medium Capacity Bombs Additional mass: 484 kg Ammunition mass: 464 kg Racks mass: 20 kg Estimated speed loss before drop: 45 km/h Estimated speed loss after drop: 12 km/h2 x 1000 lb Medium Capacity Bombs Additional mass: 969 kg Ammunition mass: 949 kg Racks mass: 20 kg Estimated speed loss before drop: 57 km/h Estimated speed loss after drop: 12 km/hSabre IIA engine with +11 lb boost Estimated speed increase at sea level: 23 km/h Operation features: - The engine is equipped with the two-stage mechanical supercharger which should be manually switched at 9500ft altitude. - The engine mixture control is automatic when the mixture lever is set to NORMAL (1/2) position. It should be set to START (forward) position when starting the engine and to CUT-OUT position (back) to stop it. - The engine has an automatic RPM governor that controls the propeller pitch to maintain the required RPM. - Water and oil temperatures are controlled manually by adjusting the radiator shutters. - The aircraft has pitch and yaw flight-control trimmers. - Landing flaps have hydraulic actuators and can be extended to any angle up to 80°. The speed with the extended flaps is limited to 160 mph. - The airplane tail wheel rotates freely and does not have a lock. - The pneumatic brakes are differential: moving the pedals with brakes pressed results in releasing the brake opposite to the pressed pedal. - The landing gear indicator lamp lights up if the throttle is set to low (less than 1/3) position with the landing gear retracted. - It is impossible to open the canopy at high speeds because of the ram air, but there is an emergency jettison handle for bailing out. - The aircraft is equipped with bottom formation lights. - The range-finding gunsight reticle can be adjusted for a given target base and range. P-47D-28 Скрытый текст Indicated stall speed in flight configuration: 178..222 km/h (111..138 mph) Indicated stall speed in takeoff/landing configuration: 139..171 km/h (86..106 mph) Dive speed limit: 805 km/h (500 mph) Maximum load factor: 11.0 G Stall angle of attack in flight configuration: 17.1 ° Stall angle of attack in landing configuration: 15.3 ° Maximum true air speed at sea level, engine mode - WEP: 557 km/h (346 mph) Maximum true air speed at 7000 m (22960 feet), engine mode - WEP: 700 km/h (435 mph) Maximum true air speed at sea level, engine mode - Combat: 502 km/h (312 mph) Maximum true air speed at 9000 m (29530 feet), engine mode - Combat: 656 km/h (407 mph) Maximum true air speed at sea level, engine mode - Cruise: 467 km/h (290 mph) Maximum true air speed at 10000 m (32800 feet), engine mode - Cruise: 619 km/h (388 mph) Service ceiling: 11580 m (38000 feet) Climb at engine mode - WEP Climb rate at sea level: 18.1 m/s (3567 feet/min) Climb rate at 3000 m (9843 feet): 17.6 m/s (3455 feet/min) Climb rate at 6000 m (19685 feet): 16.4 m/s (3226 feet/min) Climb at engine mode - Combat Climb rate at sea level: 12.1 m/s (2378 feet/min) Climb rate at 3000 m (9843 feet): 11.5 m/s (2256 feet/min) Climb rate at 6000 m (19685 feet): 10.3 m/s (2031 feet/min) Maximum performance turn at sea level: 27.5 s, at 322 km/h (200 mph) IAS. Maximum performance turn at 3000 m (9843 feet): 31.0 s, at 330 km/h (205 mph) IAS. Flight endurance at 3000 m (9843 feet): 2.4 h, at 350 km/h (217 mph) IAS. Takeoff speed: 185..200 km/h (115..125 mph) Glideslope speed: 185..210 km/h (115..130 mph) Landing speed: 175..195 km/h (110..120 mph) Landing angle: 11.9 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass and 50% of fuel. Note 4: turn times are given for WEP power. Engine: Model: R-2800-59 Maximum power in WEP mode at sea level: 2600 HP Maximum power in Combat mode at sea level: 1950 HP Maximum power in Cruise mode at sea level: 1620 HP Maximum power in WEP mode at 7000 m (22970 feet): 2600 HP Maximum power in Combat mode at 9000 m (29530 feet): 1900 HP Maximum power in Cruise mode at 10500 m (34450 feet): 1600 HP Engine modes: Cruise (unlimited time): 2550 RPM, 42.0 inch Hg Combat power (up to 15 minutes): 2700 RPM, 52 inch Hg WEP (up to 5 minutes): 2700 RPM, 64.0 inch Hg Maximum continuous turbocharger RPM: 20000 Maximum turbocharger RPM for up to 15 minutes: 22000 Oil rated temperature in engine intake: 60..95 °C Oil maximum temperature in engine intake: 100 °C Supercharger gear shift altitude: single gear Empty weight: 4755 kg (10483 lb) Minimum weight (no ammo, 10% fuel, 4 MG removed): 5163.9 kg (11385 lb) Standard weight: 6503 kg (14337 lb) Maximum takeoff weight: 8163.1 kg (17996 lb) Fuel load: 1006 kg (3095 lb) / 1404 l (370 gal) Useful load: 3408.1 kg (7514 lb) Forward-firing armament: 8 x 12.7mm machine gun "M2.50", 267 rounds, 850 rounds per minute, wing-mounted It is possible to remove 2 or 4 machine guns and/or increase the ammo load to 425 rounds per gun. Bombs: Up to three 500 lb general purpose bomb "M64" Up to two 1000 lb general purpose bomb "M65" Rockets: 6 x unguided rockets "M8" in two "M10" launchers that can be jettisoned Length: 11.00 m (36.09 feet) Wingspan: 12.43 m (40.78 feet) Wing surface: 27.87 m^2 (300 feet^2) Combat debut: 1944 Additional airplane configurations list: Скрытый текст Removal of 2 external wing-mounted machine guns to reduce total weight Removed mass: 140.3 kg (309.3 lbs) Removed ammunition mass: 75.3 kg (166.0 lbs) Removed guns mass: 65 kg (143.3 lbs) Estimated speed gain: 3 km/h (1.8 mph) Removal of 4 external wing-mounted machine guns to reduce total weight Removed mass: 280.6 kg (618.7 lbs) Removed ammunition mass: 150.6 kg (332.1 lbs) Removed guns mass: 130 kg (286.6 lbs) Estimated speed gain: 6 km/h (3.7 mph) Additional ammo for machine guns: 425 for each gun.8 machineguns: Additional mass: 178.2 kg (393 lbs) Estimated speed loss: 1 km/h6 machineguns: Additional mass: 133.6 kg (294.8 lbs) Estimated speed loss: 0 km/h4 machineguns: Additional mass: 89.1 kg (196.5 lbs) Estimated speed loss: 0 km/h Underwing and underbelly racks for bombs and rocketsRacks only: Rack mass: 30 kg (66.2 lbs) Estimated speed loss: 7 km/h (4.4 mph)3*500 lb General Purpose Bomb M64: Additional mass: 792 kg (1746.4 lbs) Ammunition mass: 762 kg (1680.2 lbs) Rack mass: 30 kg (66.2 lbs) Estimated speed loss before drop: 35 km/h (21.8 mph) Estimated speed loss after drop: 12 km/h (7.5 mph) 2*1000 lb General Purpose Bomb M65: Additional mass: 1054 kg (2324.1 lbs) Ammunition mass: 1024 kg (2257.9 lbs) Rack mass: 30 kg (66.2 lbs) Estimated speed loss before drop: 47 km/h (29.2 mph) Estimated speed loss after drop: 10 km/h (6.2 mph)6*M8 rockets in M10 jettisonable launchers: Additional mass: 179.9 kg (396.7 lbs) Ammunition mass: 115.9 kg (255.6 lbs) Racks mass: 64 kg (141.1 lbs) Estimated speed loss before launch: 27 km/h (16.8 mph) Estimated speed loss after launch: 21 km/h (13.1 mph) Estimated speed loss after drop: 8 km/h (5.0 mph) K-14A Gyro Gunsight Additional mass: 5.2 kg (11.5 lbs) Estimated speed loss: 0 km/h Bendix MN-28Y fixed loop radio compass for navigation with radio beacons Additional mass: 17,5 kg (38.6 lbs) Estimated speed loss: 1 km/h Rear view mirror Additional mass: 1 kg (2.2 lbs) Estimated speed loss: 3 km/h (1.8 mph) Operation features: - In addition to the automatic single stage supercharger, the engine is equipped with a turbocharger that the pilot can control. - The turbocharger is powered by the engine exhaust back pressure which can be set by a lever in the cockpit and maintained automatically using the throttle shutters on the exhaust pipes. - The air compressed in the turbocharger goes to the intercooler where it is cooled by the incoming airflow. The cool compressed air goes to the carburetor and the resulting fuel-air mixture goes to the supercharger. - The temperature of the air after the intercooler is indicated by a separate gauge. The pilot can control the intercooler flaps using the toggle switch and observe their position using the indicator on the left. Their default position is neutral (50%). - The turbocharger RPM is controlled by the lever in the cockpit ("T" and "+"/"-" keys by default). At the back lever position the throttle shutters are fully open and exhaust gases all go to the atmosphere, resulting in minimal turbocharger RPM. At the forward lever position, the exhaust back pressure and the resulting turbocharger RPM are at maximum. It should be noted that the RPM will change with the altitude even if the lever is kept in the same position. The turbocharger RPM is indicated by a dedicated gauge; in addition, the signal lamp will light up if the maximum RPM limit is exceeded. - The total engine power should be controlled using the joint method when the three levers - RPM lever, throttle lever and turbocharger lever are moved together. However, in certain cases (for instance, when going higher than the critical altitude) the turbocharger lever should be adjusted separately. - It should be noted that turbocharger RPM changes relatively slowly and not immediately after the control lever adjustment. - The aircraft is equipped with the water injection system that boosts the power in the emergency mode. When this system is engaged, the exhaust back pressure and turbocharger RPM increase automatically while the mixture becomes leaner. The water supply is good for around 15 minutes at the emergency power. - The engine is equipped with an automatic fuel mixture control which maintains optimal mixture if the mixture lever is set to Auto Rich (85%) position. To use automatic mixture leaning to reduce fuel consumption during flight it is necessary to set the mixture lever to Auto Lean (60%) position. In the case of malfunction of the automatic mixture control the mixture lever should be set to Full Rich (100%) position. To stop the engine mixture lever should be set to the Cut Off (0%) position. - Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM. Also, it is possible to turn off the governor and control propeller pitch manually. - Oil radiators shutters are manually operated. - The aircraft has trimmers for all flight-controls: pitch, roll and yaw. - Landing flaps have a hydraulic actuator and they can be extended to any angle up to 40°. - It is forbidden to open the cowl flaps at speeds exceeding 225 mph, perform sharp maneuvers with the opened cowl shutters and dive with the opened intercooler shutters. - The aircraft has a manual control for the tailwheel lock. The tailwheel should be locked when taxiing straight for a long distance and before takeoff and landing. - The aircraft has independent left and right hydraulic wheel brake controls. To apply either brake push the upper part of the rudder pedal. - The aircraft is equipped with a parking brake system. - The signal lamp lights up when the landing gear is up and the throttle is in the backward position or when the landing gear is down, but the throttle is in the forward position. - It should be noted that the aircraft requires a long takeoff run - around 650 meters at standard load and 1500 meters at maximum takeoff weight. It is possible to lower the flaps to 10-20 degrees to shorten the takeoff run. - The aircraft is equipped with one fuel gauge, but two indicator needles for the forward and rear fuel tanks. - The engine consumes much fuel at the combat power mode - around 4.5 gallons per minute. - The canopy has an emergency release system for bailouts. - The aircraft is equipped with the manual bomb release system for each of the three bomb racks. - The unguided rockets are launched using the electric controller which allows single, pair, triple and salvo (all rockets at 0.1 seconds interval) launch. - There is a backup mechanical sight which can be used if the main sight is damaged. - The gyroscopic gunsight automatically calculates required angular deflection while firing at a target. It has 3 modes: fixed reticle, fixed and gyro reticle, gyro reticle. The angular deflection will be calculated correctly only if the target range is set properly. To set the range, adjust the target base first using separate controls and then set the range by adjusting the size of the range-finding reticle to be the same as the target size. P-51D-15 Indicated stall speed in flight configuration: 159..196 km/h (99..122 mph) Indicated stall speed in takeoff/landing configuration: 147..181 km/h (91..112 mph) Dive speed limit: 812 km/h (505 mph) Maximum load factor: 10.0 G Stall angle of attack in flight configuration: 19.1 ° Stall angle of attack in landing configuration: 16.3 ° Maximum true air speed at sea level, engine mode - WEP: 592 km/h (368 mph) Maximum true air speed at 8000 m (26250 feet), engine mode - WEP: 717 km/h (446 mph) Maximum true air speed at sea level, engine mode - WEP, with 150 grade fuel: 607 km/h (377 mph) Maximum true air speed at 7000 m (22960 feet), engine mode - WEP, with 150 grade fuel: 718 km/h (446 mph) Maximum true air speed at sea level, engine mode - Combat: 578 km/h (359 mph) Maximum true air speed at 8500 m (28000 feet), engine mode - Combat: 711 km/h (442 mph) Maximum true air speed at sea level, engine mode - Cruise: 513 km/h (319 mph) Maximum true air speed at 8500 m (28000 feet), engine mode - Cruise: 646 km/h (401 mph) Service ceiling: 12680 m (41600 feet) Climb at engine mode - WEP Climb rate at sea level: 18.1 m/s (3567 feet/min) Climb rate at 3000 m (9843 feet): 15.7 m/s (3083 feet/min) Climb rate at 6000 m (19685 feet): 12.4 m/s (2433 feet/min) Maximum performance turn at sea level: 20.0 s, at 290 km/h (180 mph) IAS. Maximum performance turn at 3000 m (9843 feet): 29.5 s, at 295 km/h (183 mph) IAS. Flight endurance at 3000 m (9843 feet): 4.3 h, at 350 km/h (217 mph) IAS. Takeoff speed: 185..200 km/h (115..125 mph) Glideslope speed: 185..210 km/h (115..130 mph) Landing speed: 175..195 km/h (110..120 mph) Landing angle: 12.9 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass and 68% of fuel. Note 4: turn times are given for WEP power. Engine: Model: Packard V-1650-7 Maximum power in WEP mode at sea level: 1650 HP Maximum power in Combat mode at sea level: 1490 HP Maximum power in WEP mode at 5800 m (19030 feet): 1525 HP Maximum power in Combat mode at 6500 m (21325 feet): 1390 HP Engine modes: Cruise (unlimited time): 2700 RPM, 46 inch Hg Combat power (up to 15 minutes): 3000 RPM, 61 inch Hg WEP (up to 5 minutes): 3000 RPM, 67 inch Hg WEP with 150 grade fuel (up to 5 minutes): 3000 RPM, 75 inch Hg Water rated temperature in engine output: 100..110 °C Water maximum temperature in engine output: 121 °C Oil rated temperature in engine intake: 80 °C Oil maximum temperature in engine intake: 90 °C Supercharger gear shift altitude: automatic with possibility of manual switch to low gear Empty weight: 3433 kg (7568 lb) Minimum weight (no ammo, 10% fuel, 2 MG removed): 3629.5 kg (8002 lb) Standard weight: 4578.6 kg (10093 lb) Maximum takeoff weight: 5667 kg (12493 lb) Fuel load: 732 kg (1614 lb) / 1020 l (269 gal) Useful load: 2234 kg (4925 lb) Forward-firing armament: 6 x 12.7mm machine gun "M2 .50", 400 rounds for inboard and 270 rounds for central and outboard, 850 rounds per minute, wing-mounted It is possible to remove 2 central machine guns, and increase the ammo load of outboard to 500 rounds per gun It is possible to increase the ammo load of inboard to 490 rounds per gun Bombs: Up to two 500 lb general purpose bomb "M64" Up to two 1000 lb general purpose bomb "M65" Rockets: 6 x unguided rockets "M8" in two "M10" launchers that can be jettisoned Length: 9.84 m (32 3-5/16 feet) Wingspan: 11.29 m (37 5/16 feet) Wing surface: 22.30 m² (240 feet²) Combat debut: 1944 Additional airplane configurations list: Removal of 2 central wing-mounted machine guns and additional ammo for outboard machine guns: 500 for each gun. Removed mass: 70.9 kg (156 lbs) Removed ammunition mass: 9.9 kg (22 lbs) Removed guns mass: 61 kg (134 lbs) Estimated speed gain: 1 km/h (0.6 mph)Additional ammo for inboard machine guns: 490 for each gun. Additional mass: 22.4 kg (49.4 lbs) Estimated speed loss: 0 km/h2 x 500 lb M64 General Purpose Bombs Additional mass: 530 kg (1169 lb) Ammunition mass: 508 kg (1120 lb) Racks mass: 22 kg (49 lb) Estimated speed loss before drop: 25 km/h (15.5 mph) Estimated speed loss after drop: 9 km/h (5.6 mph)2 x 1000 lb M65 General Purpose Bombs Additional mass: 1046 kg (2306 lb) Ammunition mass: 1024 kg (2258 lb) Racks mass: 22 kg (49 lb) Estimated speed loss before drop: 51 km/h (31.7 mph) Estimated speed loss after drop: 9 km/h (5.6 mph)6 x M8 rockets in jettisonable M10 launchers Additional mass: 171.9 kg (379 lbs) Ammunition mass: 115.9 kg (256 lbs) Racks mass: 56 kg (123 lbs) Estimated speed loss before launch: 38 km/h (23.6 mph) Estimated speed loss after launch: 28 km/h (17.4 mph) Estimated speed loss after drop: 6 km/h (3.7 mph)K-14A Gyro Gunsight Additional mass: 5.2 kg (11.5 lbs) Estimated speed loss: 0 km/h150 grade fuel 150 grade fuel, which allows increase manifold pressure up to 75 inch.Fixed loop Bendix MN-26 radio compass for navigation with radio beacons Additional mass: 17,5 kg (38.6 lbs) Estimated speed loss: 2 km/h (1.2 mph)Rear view mirror Additional mass: 1 kg (2.2 lbs) Estimated speed loss: 2 km/h (1.2 mph) Operation features: - COMBAT, AEROBATIC MANEUVERS AND INSTRUMENT FLYING ARE FORBIDDEN AT FULL FUEL RESERVE! The aircraft is unstable with full rear fuel tank. This limit is lifted when there is no more than 20 gallons (around 75% fuel left) in the rear tank. This tank is completely empty at 68% total fuel level. - It is possible to reach dangerously high Mach numbers in a dive: the aircraft starts to shake and the loss of control is possible. Reduce the throttle and gently return to a horizontal flight. - Engine is equipped with the automatic governor of the manifold pressure that works when the throttle is set to 1/3 position or above. - Engine has a two stage mechanical supercharger which does not require manual control. It can be switched to the low gear manually. - The engine is equipped with an automatic fuel mixture control which maintains optimal mixture if the mixture lever is set to RUN (70%) position. In the case of malfunction of the automatic mixture control the mixture lever should be set to Full Rich (100%) position. To stop the engine mixture lever should be set to the Cut Off (0%) position. - Engine RPM has an automatic governor that controls the propeller pitch to maintain the required RPM. - The water and oil radiators shutters are operated automatically, but there is a manual mode. - The aircraft has trimmers for all flight-controls: pitch, roll and yaw. - Landing flaps have a hydraulic actuator and can be extended to 10°, 20°, 30°, 40° or 50°. - Each tank has a dedicated fuel level indicator: wing tank inidicators are located on the cockpit floor and the rear tank indicator is behind the pilot seat on the left. - The tail wheel rotates freely, but moving the control stick back locks it so it rotates by the pedals input. - The aircraft has independent left and right hydraulic wheel brake controls. To apply either brake push the upper part of the rudder pedal. - The aircraft is equipped with a parking brake system. - The signal lamp lights up when the landing gear is up and the throttle is in the backward position or when the landing gear is down, but the throttle is in the forward position. - Airplane is equipped with a siren that warns a pilot if the throttle is set to low position with landing gear retracted. - It is impossible to open the canopy at high speeds because of the ram air, but there is an emergency jettison handle for bailing out. - The aircraft is equipped with formation lights. - The unguided rockets are launched using the electric controller which allows single, pair, triple and salvo (all rockets at 0.1 seconds interval) launch. - The gyroscopic gunsight automatically calculates required angular deflection while firing at a target. It has 3 modes: fixed reticle, fixed and gyro reticle, gyro reticle. The angular deflection will be calculated correctly only if the target range is set properly. To set the range, adjust the target base first using separate controls and then set the range by adjusting the size of the range-finding reticle to be the same as the target size. Bf 109 G-14 Скрытый текст Indicated stall speed in flight configuration: 164..181 km/h Indicated stall speed in takeoff/landing configuration: 156..172 km/h Dive speed limit: 850 km/h Maximum load factor: 10.5 G Stall angle of attack in flight configuration: 19.8 ° Stall angle of attack in landing configuration: 17 ° Maximum true air speed at sea level, engine mode - Emergency: 576 km/h Maximum true air speed at 5500 m,, engine mode - Emergency: 668 km/h Maximum true air speed at sea level, engine mode - Combat: 505 km/h Maximum true air speed at 2000 m, engine mode - Combat: 545 km/h Maximum true air speed at 7000 m, engine mode - Combat: 619 km/h Service ceiling: 11500 m Climb rate at sea level: 19.2 m/s Climb rate at 3000 m: 17.5 m/s Climb rate at 6000 m: 13.1 m/s Maximum performance turn at sea level: 23.0 s, at 270 km/h IAS. Maximum performance turn at 3000 m: 31.5 s, at 270 km/h IAS. Flight endurance at 3000 m: 2.15 h, at 350 km/h IAS. Takeoff speed: 155..180 km/h Glideslope speed: 195..205 km/h Landing speed: 150..155 km/h Landing angle: 13.7 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates and turn times are given for Combat power. Engine: Model: DB-605AM Maximum power in Emergency mode with MW-50 at sea level: 1800 HP Maximum power in Emergency mode with MW-50 at 5600 m: 1700 HP Maximum power in Combat mode at sea level: 1310 HP Maximum power in Combat mode at 5800 m: 1250 HP Engine modes: Nominal (unlimited time): 2300 RPM, 1.15 ata Combat power (up to 30 minutes): 2600 RPM, 1.3 ata Emergency power (up to 10 minute): 2800 RPM, 1.7 ata Water rated temperature in engine output: 100..102 °C Water maximum temperature in engine output: 115 °C Oil rated temperature in engine intake: 70..80 °C Oil maximum temperature in engine intake: 85 °C Supercharger gear shift altitude: fluid coupling Empty weight: 2680 kg Minimum weight (no ammo, 10% fuel): 2899 kg Standard weight: 3266 kg Maximum takeoff weight: 3565 kg Fuel load: 304 kg / 400 l Useful load: 885 kg Forward-firing armament: 20mm gun "MG 151/20", 200 rounds, 700 rounds per minute, nose-mounted 2 x 13mm machine gun "MG 131", 300 rounds, 900 rounds per minute, synchronized 2 x 20mm gun "MG 151/20", 135 rounds, 700 rounds per minute, wing-mounted (modification) 30mm gun "MK 108", 65 rounds, 650 rounds per minute, nose-mounted (modification) Bombs: Up to 4 x 66 kg fragmentation bombs "SD 70" 249 kg general purpose bomb "SC 250" Rockets: Two WGr.21 rockets in jettisonable launchers Length: 8.94 m Wingspan: 9.97 m Wing surface: 16.1 m^2 Combat debut: July 1944 Additional airplane configurations list: Скрытый текст MK 108 30mm nose-gun with 65 rounds Additional mass: 4 kg Ammunition mass: 38 kg Gun mass: 58 kg Estimated speed loss: 0 km/h MG 151/20 20mm guns in wing-mounted gun pods with 135 rounds per each Additional mass: 212 kg Ammunition mass: 55 kg Guns mass: 157 kg Estimated speed loss: 17 km/h 4 x 66 kg fragmentation bombs SD 70 Additional mass: 304 kg Ammunition mass: 264 kg Racks mass: 40 kg Estimated speed loss before drop: 63 km/h Estimated speed loss after drop: 17 km/h 249 kg General Purpose Bomb SC 250 Additional mass: 279 kg Ammunition mass: 249 kg Racks mass: 30 kg Estimated speed loss before drop: 41 km/h Estimated speed loss after drop: 14 km/h Two 21cm WGr.21 rockets in jettisonable launchers Additional mass: 258 kg Ammunition mass: 224 kg Racks mass: 34 kg Estimated speed loss before launch: 61 km/h Estimated speed loss after launch: 14 km/h Estimated speed loss after drop: 2 km/h FuG-16ZY fixed loop radio compass for navigation with radio beacons Additional mass: 20 kg Estimated speed loss: 5 km/h Operation features: - Airplane has a wide automatization of the engine systems, in fact, to control speed it is only necessary to use the throttle lever. There is no need to manually set engine revolutions and mixture or supercharger gear in normal flight. - The aircraft is equipped with MW-50 water-methanol mixture injection system that prevents the engine detonation in the emergency power mode. It engages automatically when the throttle is set to maximum, there is enough mixture for 25-30 minutes. However, the engine can work up to 10 minutes at this mode, wait for another 10 minutes at the combat mode before engaging the emergency mode again. Attention: running the engine at the emergency mode without the water-methanol mixture or at altitudes higher than 6 km is forbidden! A pilot can check the system using the injection pressure indicator on the left: its normal pressure is 0.6...0.7 atm, stop using it if the pressure is lower than 0.4 atm and switch the engine to combat mode. - In addition to full-automatic mode there is a special manual control mode for the radiator shutters, which can be used in specific situations. - To reduce swinging during taxiing due to prop-wash the propeller pitch control should be switched to manual mode and pitch should be reduced to minimum. - Airplane has no flight-control trimmers. Airplane is equipped with bendable trim tabs that can be set pre-flight by ground personnel. - Airplane has a manually controlled horizontal stabilizer. It should be set to +1° before takeoff and to -4°...-5° before landing. Also, it may be used to trim the flight stick during the flight. In a deep dive the stabilizer should be set so that the pilot must push the flight stick forward to maintain the dive angle. - Airplane has automatic wing slats. They deploy when the high angle of attack increases which makes pre-stall softer. - Airplane has a manual mechanical system for retracting the landing flaps, for this reason it is necessary to extend landing flaps well before final approach. Markers on the left-wing flap indicate how far the flaps are extended. The flaps can be extended to any angle up to 40°. - Airplane has a manual tail wheel lock. Wheel should be locked when taxiing straight for a long distance and before takeoff and landing. - Airplane has independent left and right hydraulic wheel brake controls. To apply either brake push the upper part of the rudder pedal. - Airplane has a fuel gauge which shows total fuel remaining. Also, it has an emergency fuel warning light (80 liters). - The design of the cockpit canopy does not allow it to be opened during flight. The canopy should be closed before takeoff to prevent damage. The canopy has an emergency release system for bailouts. - The control system for the bomb rack only allows to drop bombs one by one. - The gunsight has a sliding sun-filter. Bf 109 K-4 Скрытый текст Indicated stall speed in flight configuration: 167..190 km/h Indicated stall speed in takeoff/landing configuration: 160..181 km/h Dive speed limit: 850 km/h Maximum load factor: 10.5 G Stall angle of attack in flight configuration: 19.8 ° Stall angle of attack in landing configuration: 17 ° DB-605DB engine: Maximum true air speed at sea level, engine mode - Emergency: 599 km/h Maximum true air speed at 7500 m, engine mode - Emergency: 702 km/h Maximum true air speed at sea level, engine mode - Combat: 543 km/h Maximum true air speed at 8000 m, engine mode - Combat: 684 km/h Service ceiling: 12300 m Climb rate at sea level: 20.5 m/s Climb rate at 3000 m: 17.5 m/s Climb rate at 6000 m: 13.4 m/s Maximum performance turn at sea level: 24.0 s, at 270 km/h IAS. Maximum performance turn at 3000 m: 32.2 s, at 270 km/h IAS. DB-605DC engine: Maximum true air speed at sea level, engine mode - Emergency: 614 km/h Maximum true air speed at 6200 m, engine mode - Emergency: 713 km/h Maximum true air speed at sea level, engine mode - Combat: 536 km/h Maximum true air speed at 8000 m, engine mode - Combat: 684 km/h Service ceiling: 12300 m Climb rate at sea level: 19.7 m/s Climb rate at 3000 m: 17.4 m/s Climb rate at 6000 m: 13.3 m/s Maximum performance turn at sea level: 24.2 s, at 270 km/h IAS. Maximum performance turn at 3000 m: 32.3 s, at 270 km/h IAS. Flight endurance at 3000 m: 2.15 h, at 350 km/h IAS. Takeoff speed: 160..190 km/h Glideslope speed: 200..215 km/h Landing speed: 155..160 km/h Landing angle: 12.5 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates and turn times are given for Combat power. Engine: Model: DB-605DB Maximum power in Emergency mode with MW-50 at sea level: 1850 HP Maximum power in Emergency mode with MW-50 at 6000 m: 1600 HP Maximum power in Combat mode at sea level: 1430 HP Maximum power in Combat mode at 6800 m: 1285 HP Engine modes: Nominal (unlimited time): 2400 RPM, 1.35 ata Combat power (up to 30 minutes): 2600 RPM, 1.45 ata Emergency power (up to 10 minutes): 2800 RPM, 1.8 ata Engine: Model: DB-605DC Maximum power in Emergency mode with MW-50 at sea level: 2000 HP Maximum power in Emergency mode with MW-50 at 4900 m: 1800 HP Maximum power in Combat mode at sea level: 1370 HP Maximum power in Combat mode at 6800 m: 1285 HP Engine modes: Nominal (unlimited time): 2400 RPM, 1.35 ata Combat power (up to 30 minutes): 2600 RPM, 1.45 ata Emergency power (up to 10 minutes): 2800 RPM, 1.98 ata Water rated temperature in engine output: 100..102 °C Water maximum temperature in engine output: 115 °C Oil rated temperature in engine intake: 70..80 °C Oil maximum temperature in engine intake: 95 °C Supercharger gear shift altitude: fluid coupling Empty weight: 2754 kg Minimum weight (no ammo, 10% fuel): 3006 kg Standard weight: 3361 kg Maximum takeoff weight: 3891 kg Fuel load: 304 kg / 400 l Useful load: 1137 kg Forward-firing armament: 30mm gun "MK 108", 65 rounds, 650 rounds per minute, nose-mounted 2 x 13mm machine gun "MG 131", 300 rounds, 900 rounds per minute, synchronized 2 x 20mm gun "MG 151/20", 135 rounds, 700 rounds per minute, wing-mounted (modification) Bombs: 249 kg general purpose bomb "SC 250" 500 kg general purpose bomb "SC 500" Length: 8.94 m Wingspan: 9.97 m Wing surface: 16.1 m^2 Combat debut: October 1944 Additional airplane configurations list: Скрытый текст MG 151/20 20mm guns in wing-mounted gun pods with 135 rounds per each Additional mass: 212 kg Ammunition mass: 55 kg Guns mass: 157 kg Estimated speed loss: 17 km/h 249 kg General Purpose Bomb SC 250 Additional mass: 279 kg Ammunition mass: 249 kg Racks mass: 30 kg Estimated speed loss before drop: 41 km/h Estimated speed loss after drop: 14 km/h 500 kg General Purpose Bomb SC 500 Additional mass: 530 kg Ammunition mass: 500 kg Racks mass: 30 kg Estimated speed loss before drop: 41 km/h Estimated speed loss after drop: 13 km/h DB 605 DC engine Additional mass: 0 kg Estimated speed loss: 0 km/h Operation features: - Airplane has a wide automatization of the engine systems, in fact, to control speed it is only necessary to use the throttle lever. There is no need to manually set engine revolutions and mixture or supercharger gear in normal flight. - The aircraft is equipped with MW-50 water-methanol mixture injection system that prevents the engine detonation in the emergency power mode. It engages automatically when the throttle is set to maximum, there is enough mixture for 25-30 minutes. However, the engine can work up to 10 minutes at this mode, wait for another 10 minutes at the combat mode before engaging the emergency mode again. Attention: running the engine at the emergency mode without the water-methanol mixture or at altitudes higher than 6 km is forbidden! A pilot can check the system using the injection pressure indicator on the left: its normal pressure is 0.6...0.7 atm, stop using it if the pressure is lower than 0.4 atm and switch the engine to combat mode. - In addition to full-automatic mode there is a special manual control mode for the radiator shutters, which can be used in specific situations. - To reduce swinging during taxiing due to prop-wash the propeller pitch control should be switched to manual mode and pitch should be reduced to minimum. - Airplane has no flight-control trimmers. Airplane is equipped with bendable trim tabs that can be set pre-flight by ground personnel. - Airplane has a manually controlled horizontal stabilizer. It should be set to +1° before takeoff and to -4°...-5° before landing. Also, it may be used to trim the flight stick during the flight. In a deep dive the stabilizer should be set so that the pilot must push the flight stick forward to maintain the dive angle. - Airplane has automatic wing slats. They deploy when the high angle of attack increases which makes pre-stall softer. - Airplane has a manual mechanical system for retracting the landing flaps, for this reason it is necessary to extend landing flaps well before final approach. Markers on the left-wing flap indicate how far the flaps are extended. The flaps can be extended to any angle up to 40°. - Airplane has a manual tail wheel lock. Wheel should be locked when taxiing straight for a long distance and before takeoff and landing. - Airplane has independent left and right hydraulic wheel brake controls. To apply either brake push the upper part of the rudder pedal. - Airplane has a fuel gauge which shows total fuel remaining. Also, it has an emergency fuel warning light (80 liters). - The design of the cockpit canopy does not allow it to be opened during flight. The canopy should be closed before takeoff to prevent damage. The canopy has an emergency release system for bailouts. - The gunsight has a sliding sun-filter. Fw 190 A-8 Скрытый текст Indicated stall speed in flight configuration: 177..208 km/h Indicated stall speed in takeoff/landing configuration: 164..188 km/h Dive speed limit: 850 km/h Maximum load factor: 11 G Stall angle of attack in flight configuration: 19.5° Stall angle of attack in landing configuration: 18.1° Maximum true air speed at sea level, engine mode - Emergency: 558 km/h Maximum true air speed at 3000 m, engine mode - Emergency: 580 km/h Maximum true air speed at 6200 m, engine mode - Emergency: 641 km/h Maximum true air speed at sea level, engine mode - Combat: 532 km/h Maximum true air speed at 3000 m, engine mode - Combat: 558 km/h Maximum true air speed at 5800 m, engine mode - Combat: 612 km/h Service ceiling: 10300 m Climb rate at sea level: 13.8 m/s Climb rate at 3000 m: 10.1 m/s Climb rate at 6000 m: 7.8 m/s Maximum performance turn at sea level: 24.2 s, at 280 km/h IAS. Maximum performance turn at 3000 m: 33.0 s, at 280 km/h IAS. Flight endurance at 3000 m: 3.8 h, at 350 km/h IAS. Takeoff speed: 180..220 km/h Glideslope speed: 215..225 km/h Landing speed: 160..180 km/h Landing angle: 12.5° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates are given for Combat power, turn times are given for Emergency power. Engine: Model: BMW-801D Maximum power in Emergency mode at sea level: 1700 HP Maximum power in Emergency mode at 5700 m: 1440 HP Maximum power in Combat mode at 700 m: 1520 HP Maximum power in Combat mode at 5300 m: 1320 HP Engine modes: Nominal (unlimited time): 2300 RPM, 1.2 ata Combat power (up to 30 minutes): 2400 RPM, 1.32 ata Emergency power (up to 3 minutes): 2700 RPM, 1.42 ata Oil rated temperature in engine intake: 60..70 °C Oil maximum temperature in engine intake: 85 °C Oil rated temperature in engine output: 105 °C Oil maximum temperature in engine output: 120 °C Cylinder head rated temperature: 180 °C Cylinder head maximum temperature: 220 °C Supercharger gear shift altitude: automatic Empty weight: 3504 kg Minimum weight (no ammo, 10% fuel): 3697 kg Standard weight: 4391 kg Maximum takeoff weight: 5239 kg Fuel load: 498 kg / 639 l Useful load: 1735 kg Forward-firing armament: 2 x 20mm gun "MG 151/20", 250 rounds, 700 rounds per minute, synchronized 2 x 20mm gun "MG 151/20", 140 rounds, 700 rounds per minute, wing-mounted 2 x 13mm machine gun "MG 131", 475 rounds, 900 rounds per minute, synchronized 2 x 30mm gun "MK 108", 55 rounds, 650 rounds per minute, wing-mounted (modification) Bombs: Up to 8 x 66 kg fragmentation bombs "SD 70" Up to 3 x 249 kg general purpose bomb "SC 250" 500 kg general purpose bomb "SC 500" 1090 kg general purpose bomb "SC 1000" Rockets: Two WGr.21 rockets in jettisonable launchers Up to 12 Panzerblitz 1 rockets (R-HL, M8) Length: 8.85 m Wingspan: 10.51 m Wing surface: 18.3 m^2 Combat debut: Spring 1944 Additional airplane configurations list: Скрытый текст Two MK 108 30mm wing-mounted guns with 55 rounds per gun Additional mass: 63 kg Ammunition mass: 64 kg Guns mass: 116 kg Estimated speed loss: 0 km/h TC 501 Central Bombholder4 x 66 kg Fragmentation Bombs SD 70: Additional mass: 324 kg Ammunition mass: 264 kg Racks mass: 60 kg Estimated speed loss before drop: 93 km/h Estimated speed loss after drop: 46 km/h249 kg General Purpose Bomb SC 250: Additional mass: 279 kg Ammunition mass: 249 kg Racks mass: 30 kg Estimated speed loss before drop: 43 km/h Estimated speed loss after drop: 16 km/h500 kg General Purpose Bomb SC 500: Additional mass: 530 kg Ammunition mass: 500 kg Racks mass: 30 kg Estimated speed loss before drop: 48 km/h Estimated speed loss after drop: 16 km/h1090 kg General Purpose Bomb SC 1000: Additional mass: 1120 kg Ammunition mass: 1090 kg Racks mass: 30 kg Estimated speed loss before drop: 85 km/h Estimated speed loss after drop: 28 km/h Two 21cm WGr.21 rockets in jettisonable launchers Additional mass: 258 kg Ammunition mass: 224 kg Racks mass: 34 kg Estimated speed loss before launch: 67 km/h Estimated speed loss after launch: 16 km/h Estimated speed loss after drop: 4 km/h Additional protection: side armour plates and armoured glass on the windshield sides. Additional mass: 85 kg Estimated speed loss: 5 km/h Fw 190 F-8 / G-8 Fw 190 F-8 "Schlachtflugzeug" strike modification includes additional fuselage bottom and engine armour, 70 kg underwing bomb or rocket holders and removes the outer MG151/20 wing-mounted guns. Fw 190 G-8 "Jabo-Rei" bomber modification is enabled when "Removal of MG 131" is also selected. This modification also allows to attach 250 kg underwing bombs. Additional mass: 68 kg Estimated speed loss: 17 km/h Removal of 2 nose-mounted 13mm MG 131 machine guns (only together with "Sturmjäger" or "F-8/G-8" modifications). In combination with "F-8/G-8" modification it allows to carry one SC 1000 or two SC 250 bombs. Removed ammunition mass: 81 kg Removed guns mass: 40 kg Operation features: - Airplane has a wide automatization of the engine systems, in fact, to control speed it is only necessary to use the throttle lever. There is no need to manually set engine revolutions and mixture or supercharger gear in normal flight. The engine supercharger has an automatic switch system which depends on altitude and engine revolutions. - There is an additional emergency engine mode system installed. When it is engaged, the first supercharger gear pressure increases to 1.58 ATA and the second gear pressure to 1.65 ATA, the time limit is 10 minutes. This system is turned on by the engine boost command and works only when the throttle is set to 100%, automatic propeller pitch system is engaged and the altitude is lower than critical altitude for a given supercharger gear. - Outlet cowl shutters are operated manually. - To reduce swinging during taxiing due to prop-wash the propeller pitch control should be switched to manual mode and pitch should be reduced to minimum. - When the angle of attack increases to critical levels the wing may stall suddenly and unexpectedly. There is almost no pre-stall buffet before the stalling. To avoid this the pilot must pay additional attention when performing extreme maneuvering. - Airplane has no flight-control trimmers. Airplane is equipped with bendable trim tabs that can be set pre-flight by ground personnel. - Airplane has a manually controlled horizontal stabilizer which is electrically-actuated. It should be set to +1.5° before takeoff and landing. Also, it may be used to trim the flight stick during the flight. In a deep dive the stabilizer should be set so that the pilot must push the flight stick forward to maintain the dive angle. - Airplane has electrically-actuated landing flaps with three fixed positions: retracted, takeoff (13°) and landing (58°). Flaps control buttons are located on left panel near the throttle. The flap angle may be checked by indicators on the left and right wing outside the cockpit. - Airplane has a tail wheel lock system which locks the tail wheel if the flight-stick is pulled backward. The tailwheel should be locked when taxiing straight for a long distance, before takeoff and after touchdown upon landing. - Airplane has independent left and right hydraulic wheel brake controls. To apply either brake push the upper part of the rudder pedal. - Airplane has a fuel gauge which shows the amount of remaining fuel in the front or rear fuel tank depending on switch position. In game the fuel indicator switch changes by itself during horizontal flight by every 10 seconds. Also, the airplane has an emergency fuel warning light (100 liters). - It is impossible to open or close the canopy at high speed due to strong airflow. The canopy has an emergency release system for bailouts. - The standard bomb release controller (without modification) allows dropping the bombs only one by one. The strike modification (F-8) bomb release controller allows to choose the bomb release order for underbelly and underwing bombs and the delay between each bomb in the salvo. - The gunsight has a sliding sun-filter. Me 262 A Indicated stall speed in flight configuration: 165..200 km/h Indicated stall speed in takeoff/landing configuration: 139..154 km/h Dive true air speed limit: 1000 km/h Maximum load factor: 12.5 G Stall angle of attack in flight configuration: 17° Stall angle of attack in flight configuration (with slats extended): 23° Stall angle of attack in landing configuration: 22° Maximum true air speed at sea level, engine mode - Nominal, 8400 RPM: 759 km/h Maximum true air speed at 6000 m, engine mode - Nominal, 8400 RPM: 780 km/h Maximum true air speed at 9000 m, engine mode - Nominal, 8400 RPM: 739 km/h Maximum true air speed at sea level, engine mode - Maximal, 8700 RPM: 837 km/h Maximum true air speed at 6000 m, engine mode - Maximal, 8700 RPM: 871 km/h Maximum true air speed at 9000 m, engine mode - Maximal, 8700 RPM: 838 km/h Service ceiling: 12000 m Climb rate at sea level: 19.3 m/s Climb rate at 6000 m: 9.7 m/s Climb rate at 9000 m: 5.4 m/s Maximum performance turn at sea level: 32..35 s, at 450 km/h IAS. Maximum performance turn at 6000 m: 43..48 s, at 380 km/h IAS. Flight endurance at 6000 m: 2 h 20 m, at 475 km/h IAS. Takeoff speed: 200..220 km/h Glideslope speed: 250 km/h Landing speed: 165..185 km/h Landing angle: 12.3° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates and turn times are given for Maximal (8700 RPM) power. Engine: 2 x turbo jet Model: Jumo-004 B1 Maximum power in Maximal mode (8700 RPM) at sea level: 810 kg(f) Maximum power in Maximal mode (8700 RPM) at 6000 m: 530 kg(f) Maximum power in Maximal mode (8700 RPM) at 9000 m: 385 kg(f) Engine modes: Nominal (unlimited time): 8400 RPM Maximal (15 minutes): 8700 RPM Nominal exhaust temperature: 600 °C Maximum exhaust temperature: 650 °C Exhaust pressure: 0.2-0.38 kg/s² Fuel injection pressure: 40-80 kg/s² Oil rated pressure in engine output: 2 kg/s² Oil maximum pressure in engine output: 5 kg/s² Empty weight: 4146 kg Minimum weight (no ammo, 10% fuel): 4737 kg Standard weight: 6400 kg Weight with full tanks: 6900 kg Maximum takeoff weight: 7100 kg Fuel load: 2161 kg / 2570 l Useful load: 700 kg Forward-firing armament: 2 x 30mm gun "MK 108", 100 rounds, 650 rounds per minute, nose-mounted inner (upper) 2 x 30mm gun "MK 108", 80 rounds, 650 rounds per minute, nose-mounted outer (lower) Bombs: 2 x 249 kg general purpose bombs "SC 250" 500 kg general purpose bombs "SC 500" Length: 10.6 m Wingspan: 12.6 m Wing surface: 20.4 m² Combat debut: Summer 1944 Additional airplane configurations list: EZ42 Gyro Gunsight Additional mass: 13 kg Estimated speed loss: 0 km/h24 x 55 mm High Explosive unguided rockets R4M Additional mass: 90 kg Ammunition mass: 73 kg Racks mass: 17 kg Estimated speed loss before launch: 70 km/h Estimated speed loss after launch: 36 km/hPilot armoured headrest Additional mass: 33 kg Estimated speed loss: 0 km/hPilot back armor Additional mass: 59 kg Estimated speed loss: 0 km/hRemoved cannons front armor Removed mass: 124 kg Estimated speed gain: 2 km/hRemoved two inner (upper) MK-108 cannons Removed mass: 244 kg Removed ammunition mass: 119 kg Removed guns mass: 125 kg Estimated speed gain: 9 km/hBomb load1 x 249 kg General Purpose Bomb SC 250 Additional mass: 279 kg Ammunition mass: 249 kg Racks mass: 30 kg Estimated speed loss before drop: 124 km/h Estimated speed loss after drop: 76 km/h2 x 249 kg General Purpose Bomb SC 250 Additional mass: 558 kg Ammunition mass: 498 kg Racks mass: 60 kg Estimated speed loss before drop: 154 km/h Estimated speed loss after drop: 100 km/h1 x 500 kg General Purpose Bomb SC 500 Additional mass: 530 kg Ammunition mass: 500 kg Racks mass: 30 kg Estimated speed loss before drop: 136 km/h Estimated speed loss after drop: 76 km/hFuel regulating valve Automatic valve in the fuel line limits an excessive fuel pressure caused by a rapid throttle increase, preventing the overheating and the resulting destruction of the engine. It almost completely removed the danger of engine fire from careless throttle inputs. It was installed on Jumo-004 B1 engines during routine maintenance since the end of 1944. Operation features: - The aircraft is equipped with two turbojet engines Jumo-004 B1. They are controlled automatically by the throttle which sets the turbine rotor RPM. - The engine is equipped with automatic fuel regulator that engaged only at more than 6000 RPM. Therefore, the fuel regulation at lower RPM wasn\'t effective and a careless throttle increase could cause excessive fuel intake, resulting in overheating and possible engine fire. - At high altitudes it is possible to lean the mixture too much by a sharp throttle decrease, causing a flameout and engine stop. The turbine shouldn\'t be set below 6000-8000 RPM depending on the altitude. - It is impossible to restart the engine at high altitudes (more than 4000 m). - The aircraft is equipped with horizontal stabilizer and rudder trim to reduce the load on controls. - The aircraft is susceptible to Mach tuck when diving at 0.84 M or higher speed. - Landing flaps have a hydraulic actuator and they can be extended to any angle up to 55°. The hydraulic valve controlling the flaps can\'t be turned during the landing gear operation (lowering or retracting). - Landing gear brakes are hydraulic as well and are engaged by pushing a corresponding pedal. The nose gear orients by itself (up to 50° in either direction), has a rotation dampener and dedicated brake handle. The aircraft tends to rotate during a breakaway unless the nose wheel is set forward. - There are two main (900 l each) and two secondary fuel tanks (600 and 170 l). The fuel transfer from secondary to main tanks using the electric fuel pump is initiated by the pilot when the fuel level in main tanks drops lower than 600 l. The main tanks have fuel level indicators and emergency fuel lamps (they light up when there are less than 250 l left). Airplanes of "Battle of Normandy": Bf 109 G-6 Late Скрытый текст Indicated stall speed in flight configuration: 161..179 km/h Indicated stall speed in takeoff/landing configuration: 153..170 km/h Dive speed limit: 850 km/h Maximum load factor: 10.5 G Stall angle of attack in flight configuration: 19.8 ° Stall angle of attack in landing configuration: 17 ° Maximum true air speed at sea level, engine mode - Emergency (with MW-50): 573 km/h (modification) Maximum true air speed at 5000 m, engine mode - Emergency (with MW-50): 661 km/h (modification) Maximum true air speed at sea level, engine mode - Emergency: 528 km/h Maximum true air speed at 6600 m, engine mode - Emergency: 631 km/h Maximum true air speed at sea level, engine mode - Combat: 508 km/h Maximum true air speed at 2000 m, engine mode - Combat: 547 km/h Maximum true air speed at 6600 m, engine mode - Combat: 618 km/h Service ceiling: 11800 m Climb rate at sea level: 20.6 m/s Climb rate at 3000 m: 18.3 m/s Climb rate at 6000 m: 14.1 m/s Maximum performance turn at sea level: 21.7 s, at 270 km/h IAS. Maximum performance turn at 3000 m: 27.4 s, at 270 km/h IAS. Flight endurance at 3000 m: 2.3 h, at 350 km/h IAS. Takeoff speed: 155..180 km/h Glideslope speed: 195..205 km/h Landing speed: 150..155 km/h Landing angle: 13.7 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates and turn times are given for Combat power. Engine: Model: DB-605A Maximum power in Emergency mode (with MW-50) at sea level: 1800 HP (modification) Maximum power in Emergency mode (with MW-50) at 4100 m: 1700 HP (modification) Maximum power in Emergency mode at sea level: 1480 HP Maximum power in Emergency mode at 5600 m: 1360 HP Maximum power in Combat mode at sea level: 1310 HP Maximum power in Combat mode at 5800 m: 1250 HP Engine modes: Nominal (unlimited time): 2300 RPM, 1.15 ata Combat power (up to 30 minutes): 2600 RPM, 1.3 ata Emergency power (up to 1 minute): 2800 RPM, 1.42 ata Emergency power (up to 10 minute with MW-50): 2800 RPM, 1.7 ata (modification) Water rated temperature in engine output: 100..102 °C Water maximum temperature in engine output: 115 °C Oil rated temperature in engine intake: 70..80 °C Oil maximum temperature in engine intake: 85 °C Supercharger gear shift altitude: fluid coupling Empty weight: 2536 kg Minimum weight (no ammo, 10%25 fuel): 2779 kg Standard weight: 3146 kg Maximum takeoff weight: 3538 kg Fuel load: 304 kg / 400 l Useful load: 1002 kg Forward-firing armament: 20mm gun "MG 151/20", 200 rounds, 700 rounds per minute, nose-mounted 2 x 13mm machine gun "MG 131", 300 rounds, 900 rounds per minute, synchronized 2 x 20mm gun "MG 151/20", 135 rounds, 700 rounds per minute, wing-mounted (modification) 30mm gun "MK 108", 65 rounds, 650 rounds per minute, nose-mounted (modification) Bombs: Up to 4 x 66 kg fragmentation bombs "SD 70" 249 kg general purpose bomb "SC 250" Rockets: Two WGr.21 rockets in jettisonable launchers Length: 8.94 m Wingspan: 9.97 m Wing surface: 16.1 m² Combat debut: early 1944 Additional airplane configurations list: Скрытый текст Two WGr.21 rockets in jettisonable launchersAdditional mass: 258 kg Ammunition mass: 224 kg Racks mass: 34 kg Estimated speed loss before launch: 51 km/h Estimated speed loss after launch: 11 km/h Estimated speed loss after drop: 2 km/h Erla Haube canopy retrofit modification Removed mass: 9 kg Estimated speed loss: 0 km/h MG 151/20 20mm guns in wing-mounted gun pods with 135 rounds per eachAdditional mass: 212 kg Ammunition mass: 55 kg Guns mass: 157 kg Estimated speed loss: 13 km/h MK 108 30mm nose-gun with 65 rounds Additional mass: 4 kg Ammunition mass: 38 kg Gun mass: 58 kg Estimated speed loss: 0 km/h MW-50 water-methanol mixture injection system Additional mass: 84 kg Water-methanol mixture mass: 63 kg Estimated speed increase at sea level: 45 km/h 249 kg General Purpose Bomb SC 250 Additional mass: 279 kg Ammunition mass: 249 kg Racks mass: 30 kg Estimated speed loss before drop: 33 km/h Estimated speed loss after drop: 11 km/h 4 x 66 kg fragmentation bombs SD 70 Additional mass: 304 kg Ammunition mass: 264 kg Racks mass: 40 kg Estimated speed loss before drop: 52 km/h Estimated speed loss after drop: 12 km/h Operation features: - Airplane has a wide automatization of the engine systems, in fact, to control speed it is only necessary to use the throttle lever. There is no need to manually set engine revolutions and mixture or supercharger gear in normal flight. - MW-50 water-methanol mixture injection system that prevents the engine detonation in the emergency power mode (modification). It engages automatically when the throttle is set to maximum, there is enough mixture for 25-30 minutes. However, the engine can work up to 10 minutes at this mode, wait for another 10 minutes at the combat mode before engaging the emergency mode again. Attention: running the engine at the emergency mode without the water-methanol mixture or at altitudes higher than 6 km is forbidden! A pilot can check the system using the injection pressure indicator on the left: its normal pressure is 0.6...0.7 atm, stop using it if the pressure is lower than 0.4 atm and switch the engine to combat mode. - In addition to full-automatic mode there is a special manual control mode for the radiator shutters, which can be used in specific situations. - To reduce swinging during taxiing due to prop-wash the propeller pitch control should be switched to manual mode and pitch should be reduced to minimum. - Airplane has no flight-control trimmers. Airplane is equipped with bendable trim tabs that can be set pre-flight by ground personnel. - Airplane has a manually controlled horizontal stabilizer. It should be set to +1° before takeoff and to -4°...-5° before landing. Also, it may be used to trim the flight stick during the flight. In a deep dive the stabilizer should be set so that the pilot must push the flight stick forward to maintain the dive angle. - Airplane has automatic wing slats. They deploy when the high angle of attack increases which makes pre-stall softer. - Airplane has a manual mechanical system for retracting the landing flaps, for this reason it is necessary to extend landing flaps well before final approach. Markers on the left-wing flap indicate how far the flaps are extended. The flaps can be extended to any angle up to 40°. - Airplane has a manual tail wheel lock. Wheel should be locked when taxiing straight for a long distance and before takeoff and landing. - Airplane has independent left and right hydraulic wheel brake controls. To apply either brake push the upper part of the rudder pedal. - Airplane has a fuel gauge which shows total fuel remaining. Also, it has an emergency fuel warning light (80 liters). - The design of the cockpit canopy does not allow it to be opened during flight. The canopy should be closed before takeoff to prevent damage. The canopy has an emergency release system for bailouts. - The control system for the bomb rack only allows to drop bombs one by one. - The gunsight has a sliding sun-filter. Fw 190 A-6 Indicated stall speed in flight configuration: 170..197 km/h Indicated stall speed in takeoff/landing configuration: 156..178 km/h Dive speed limit: 850 km/h Maximum load factor: 11 G Stall angle of attack in flight configuration: 19.5° Stall angle of attack in landing configuration: 18.1° Maximum true air speed at sea level, engine mode - Emergency: 563 km/h Maximum true air speed at 3000 m, engine mode - Emergency: 585 km/h Maximum true air speed at 6400 m, engine mode - Emergency: 661 km/h Maximum true air speed at sea level, engine mode - Combat: 535 km/h Maximum true air speed at 3000 m, engine mode - Combat: 560 km/h Maximum true air speed at 6000 m, engine mode - Combat: 622 km/h Service ceiling: 10400 m Climb rate at sea level: 15.0 m/s Climb rate at 3000 m: 11.3 m/s Climb rate at 6000 m: 8.9 m/s Maximum performance turn at sea level: 23.5 s, at 280 km/h IAS. Maximum performance turn at 3000 m: 35.5 s, at 280 km/h IAS. Flight endurance at 3000 m: 3.0 h, at 350 km/h IAS. Takeoff speed: 170..210 km/h Glideslope speed: 205..215 km/h Landing speed: 160..170 km/h Landing angle: 12.5° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates are given for Combat power, turn times are given for Emergency power. Engine: Model: BMW-801D Maximum power in Emergency mode at sea level: 1700 HP Maximum power in Emergency mode at 5700 m: 1440 HP Maximum power in Combat mode at 700 m: 1520 HP Maximum power in Combat mode at 5300 m: 1320 HP Engine modes: Nominal (unlimited time): 2300 RPM, 1.2 ata Combat power (up to 30 minutes): 2400 RPM, 1.32 ata Emergency power (up to 3 minutes): 2700 RPM, 1.42 ata Oil rated temperature in engine intake: 60..70 °C Oil maximum temperature in engine intake: 85 °C Oil rated temperature in engine output: 105 °C Oil maximum temperature in engine output: 120 °C Cylinder head rated temperature: 180 °C Cylinder head maximum temperature: 220 °C Supercharger gear shift altitude: automatic Empty weight: 3371 kg Minimum weight (no ammo, 10%25 fuel): 3553 kg Standard weight: 4140 kg Maximum takeoff weight: 4766 kg Fuel load: 409 kg / 524 l Useful load: 1395 kg Forward-firing armament: 2 x 7.92mm machine gun "MG 17", 900 rounds, 1200 rounds per minute, synchronized 2 x 20mm gun "MG 151/20", 250 rounds, 700 rounds per minute, synchronized 2 x 20mm gun "MG 151/20", 140 rounds, 700 rounds per minute, wing-mounted Bombs: Up to 8 x 66 kg general purpose bombs "SD 70" Up to 3 x249 kg general purpose bomb "SC 250" 500 kg general purpose bomb "SC 500" Rockets: Two WGr.21 rockets in jettisonable launchers Length: 8.85 m Wingspan: 10.51 m Wing surface: 18.3 m² Combat debut: Summer 1943 Additional airplane configurations list: Underwing (G-3) and underbelly racks with bombs ETC 501 Centerline Bomb Rack 4 x 66 kg Fragmentation Bombs SD 70: Additional mass: 324 kg Ammunition mass: 264 kg Racks mass: 60 kg Estimated speed loss before drop: 90 km/h Estimated speed loss after drop: 46 km/h 249 kg General Purpose Bomb SC 250: Additional mass: 279 kg Ammunition mass: 249 kg Racks mass: 30 kg Estimated speed loss before drop: 43 km/h Estimated speed loss after drop: 17 km/h 500 kg General Purpose Bomb SC 500: Additional mass: 530 kg Ammunition mass: 500 kg Racks mass: 30 kg Estimated speed loss before drop: 47 km/h Estimated speed loss after drop: 17 km/h Two WGr.21 rockets in jettisonable launchers Additional mass: 222 kg Ammunition mass: 188 kg Racks mass: 34 kg Estimated speed loss before launch: 66 km/h Estimated speed loss after launch: 17 km/h Estimated speed loss after drop: 6 km/h Fw 190 G-3 strike modification includes 250 kg underwing bomb racks, underbelly ETC 501 rack, 1.65 ATA modified engine (C3 system) and removes the outer MG151/20 wing-mounted guns and MG-17 machineguns. Removed mass: 151 kg Estimated speed loss: 27 km/h Fw 190 G-3/R-5 strike modification includes 70 kg underwing bomb racks, underbelly ETC 501 rack, 1.65 ATA modified engine (C3 system) and removes the outer MG151/20 wing-mounted guns and MG-17 machineguns (machineguns can be installed back by special modification). Removed mass: 151 kg Estimated speed loss: 29 km/h Removal of 2 wing-mounted 20mm MG-151/20 guns (not compatible with "G-3" or "G-3/R-5" modifications). Removed ammunition mass: 62 kg Removed guns mass: 87 kg Installation of 2 nose-mounted 7.92mm machine guns MG-17 (only together with "Sturmjager" or "G-3/R-5" modifications). Additional ammunition mass: 52 kg Additional guns mass: 20 kg Additional protection: side armour plates and armoured glass on the windshield and canopy sides. Machineguns are removed. Additional mass: 34 kg Estimated speed loss: 5 km/h Operation features: - Airplane has a wide automatization of the engine systems, in fact, to control speed it is only necessary to use the throttle lever. There is no need to manually set engine revolutions and mixture or supercharger gear in normal flight. The engine supercharger has an automatic switch system which depends on altitude and engine revolutions. - G-3 and G-3/R-5 modification includes C3 additional fuel injection system. When engaged, it increases pressure to 1.65 ATA (10 minutes time limit). This system can be turned on by engine boost command only at 100%25 throttle, with automatic propeller pitch control enabled and at altitudes lower than 1 km. - Outlet cowl shutters are operated manually. - To reduce swinging during taxiing due to prop-wash the propeller pitch control should be switched to manual mode and pitch should be reduced to minimum. - When the angle of attack increases to critical levels the wing may stall suddenly and unexpectedly. There is almost no pre-stall buffet before the stalling. To avoid this the pilot must pay additional attention when performing extreme maneuvering. - Airplane has no flight-control trimmers. Airplane is equipped with bendable trim tabs that can be set pre-flight by ground personnel. - Airplane has a manually controlled horizontal stabilizer which is electrically-actuated. It should be set to +1.5° before takeoff and landing. Also, it may be used to trim the flight stick during the flight. In a deep dive the stabilizer should be set so that the pilot must push the flight stick forward to maintain the dive angle. - Airplane has electrically-actuated landing flaps with three fixed positions: retracted, takeoff (13°) and landing (58°). Flaps control buttons and indicator lights are located on left panel near the throttle. The flap angle may also be checked by indicators on the left and right wing outside the cockpit. - Airplane has a tail wheel lock system which locks the tail wheel if the flight-stick is pulled backward. The tailwheel should be locked when taxiing straight for a long distance, before takeoff and after touchdown upon landing. - Airplane has independent left and right hydraulic wheel brake controls. To apply either brake push the upper part of the rudder pedal. - Airplane has a fuel gauge which shows the amount of remaining fuel in the front or rear fuel tank depending on switch position. In game the fuel indicator switch changes by itself during horizontal flight by every 10 seconds. Also, the airplane has an emergency fuel warning light (100 liters). - It is impossible to open or close the canopy at high speed due to strong airflow. The canopy has an emergency release system for bailouts. - The control system for the bomb rack only allows for dropping bombs one by one. With "G-3" and "G-3/R-5" modifications it is possible to select left, right or both underwing bomb racks, but the centerline bomb rack is always selected and each push of the bomb release control will drop one of its bombs. - The gunsight has a sliding sun-filter. P-47D-22 Indicated stall speed in flight configuration: 175..212 km/h (109..131 mph) Indicated stall speed in takeoff/landing configuration: 143..174 km/h (89..108 mph) Dive speed limit: 805 km/h (500 mph) Maximum load factor: 11.0 G Stall angle of attack in flight configuration: 16.2 ° Stall angle of attack in landing configuration: 15.4 ° Maximum true air speed at sea level, engine mode - WEP: 575 km/h (357 mph) Maximum true air speed at 7000 m (22960 feet), engine mode - WEP: 727 km/h (451 mph) Maximum true air speed at sea level, engine mode - Combat: 518 km/h (322 mph) Maximum true air speed at 9000 m (29530 feet), engine mode - Combat: 685 km/h (426 mph) Maximum true air speed at sea level, engine mode - Cruise: 485 km/h (301 mph) Maximum true air speed at 10000 m (32800 feet), engine mode - Cruise: 651 km/h (404 mph) Service ceiling: 11580 m (38000 feet) Climb at engine mode - WEP Climb rate at sea level: 18.5 m/s (3642 feet/min) Climb rate at 3000 m (9843 feet): 18.1 m/s (3559 feet/min) Climb rate at 6000 m (19685 feet): 16.9 m/s (3338 feet/min) Climb at engine mode - Combat Climb rate at sea level: 12.6 m/s (2480 feet/min) Climb rate at 3000 m (9843 feet): 11.9 m/s (2342 feet/min) Climb rate at 6000 m (19685 feet): 10.7 m/s (2106 feet/min) Maximum performance turn at sea level: 27.0 s, at 322 km/h (200 mph) IAS. Maximum performance turn at 3000 m (9843 feet): 30.0 s, at 330 km/h (205 mph) IAS. Flight endurance at 3000 m (9843 feet): 2 h, at 370 km/h (230 mph) IAS. Takeoff speed: 177..210 km/h (110..130 mph) Glideslope speed: 179..220 km/h (111..135 mph) Landing speed: 175..205 km/h (110..127 mph) Landing angle: 11.9 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass and 50%25 of fuel. Note 4: turn times are given for WEP power. Engine: Model: R-2800-59 Maximum power in WEP mode at sea level: 2600 HP Maximum power in Combat mode at sea level: 1950 HP Maximum power in Cruise mode at sea level: 1620 HP Maximum power in WEP mode at 7000 m (22970 feet): 2600 HP Maximum power in Combat mode at 9000 m (29530 feet): 1900 HP Maximum power in Cruise mode at 10500 m (34450 feet): 1600 HP Engine modes: Cruise (unlimited time): 2550 RPM, 42.0 inch Hg Combat power (up to 15 minutes): 2700 RPM, 52.0 inch Hg WEP (up to 5 minutes): 2700 RPM, 64.0 inch Hg Maximum continuous turbocharger RPM: 20000 Maximum turbocharger RPM for up to 15 minutes: 22000 Oil rated temperature in engine intake: 60..95 °C Oil maximum temperature in engine intake: 100 °C Supercharger gear shift altitude: single gear Empty weight: 4665 kg (10285 lb) Minimum weight (no ammo, 10%25 fuel, 4 MG removed): 5033 kg (11096 lb) Standard weight: 6213 kg (13697 lb) Maximum takeoff weight: 7867 kg (17343 lb) Fuel load: 829 kg (2551 lb) / 1155 l (305 gal) Useful load: 3202 kg (7058 lb) Forward-firing armament: 8 x 12.7mm machine gun "M2.50", 267 rounds, 850 rounds per minute, wing-mounted It is possible to remove 2 or 4 machine guns and/or increase the ammo load to 425 rounds per gun. Bombs: Up to three 500 lb general purpose bomb "M64" Up to two 1000 lb general purpose bomb "M65" Rockets: 6 x unguided rockets "M8" in two "M10" launchers that can be jettisoned Length: 11.00 m (36.09 feet) Wingspan: 12.43 m (40.78 feet) Wing surface: 27.87 m² (300 feet²) Combat debut: 1944 Additional airplane configurations list: 150 grade fuel 150 grade fuel, which allows increased manifold pressure up to 70 inches. Additional ammo for machine guns: 425 for each gun. 8 machineguns: Additional mass: 178.2 kg (393 lbs) Estimated speed loss: 1 km/h 6 machineguns: Additional mass: 133.6 kg (294.8 lbs) Estimated speed loss: 0 km/h 4 machineguns: Additional mass: 89.1 kg (196.5 lbs) Estimated speed loss: 0 km/h Underwing and underbelly racks for bombs and rockets Racks only: Rack mass: 30 kg (66.2 lbs) Estimated speed loss: 7 km/h (4.4 mph) 3*500 lb General Purpose Bomb M64: Additional mass: 792 kg (1746.4 lbs) Ammunition mass: 762 kg (1680.2 lbs) Rack mass: 30 kg (66.2 lbs) Estimated speed loss before drop: 35 km/h (21.8 mph) Estimated speed loss after drop: 12 km/h (7.5 mph) 2*1000 lb General Purpose Bomb M65: Additional mass: 1054 kg (2324.1 lbs) Ammunition mass: 1024 kg (2257.9 lbs) Rack mass: 30 kg (66.2 lbs) Estimated speed loss before drop: 47 km/h (29.2 mph) Estimated speed loss after drop: 10 km/h (6.2 mph) 6*M8 rockets in M10 jettisonable launchers: Additional mass: 179.9 kg (396.7 lbs) Ammunition mass: 115.9 kg (255.6 lbs) Racks mass: 64 kg (141.1 lbs) Estimated speed loss before launch: 27 km/h (16.8 mph) Estimated speed loss after launch: 21 km/h (13.1 mph) Estimated speed loss after drop: 8 km/h (5.0 mph) Removal of 4 external wing-mounted machine guns to reduce total weight Removed mass: 280.6 kg (618.7 lbs) Removed ammunition mass: 150.6 kg (332.1 lbs) Removed guns mass: 130 kg (286.6 lbs) Estimated speed gain: 6 km/h (3.7 mph) Removal of 2 external wing-mounted machine guns to reduce total weight Removed mass: 140.3 kg (309.3 lbs) Removed ammunition mass: 75.3 kg (166.0 lbs) Removed guns mass: 65 kg (143.3 lbs) Estimated speed gain: 3 km/h (1.8 mph) Fixed loop radio compass for navigation with radio beacons Additional mass: 17,5 kg (38.6 lbs) Estimated speed loss: 1 km/h Operation features: - In addition to the automatic single stage supercharger, the engine is equipped with a turbocharger that the pilot can control. - The turbocharger is powered by the engine exhaust back pressure which can be set by a lever in the cockpit and maintained automatically using the throttle shutters on the exhaust pipes. - The air compressed in the turbocharger goes to the intercooler where it is cooled by the incoming airflow. The cool compressed air goes to the carburetor and the resulting fuel-air mixture goes to the supercharger. - The temperature of the air after the intercooler is indicated by a separate gauge. The pilot can control the intercooler flaps using the toggle switch and observe their position using the indicator on the left. Their default position is neutral (50%25). - The turbocharger RPM is controlled by the lever in the cockpit ("Left Shift" and "+"/"-" keys by default). At the back lever position the throttle shutters are fully open and exhaust gases all go to the atmosphere, resulting in minimal turbocharger RPM. At the forward lever position, the exhaust back pressure and the resulting turbocharger RPM are at maximum. It should be noted that the RPM will change with the altitude even if the lever is kept in the same position. The turbocharger RPM is indicated by a dedicated gauge. - The total engine power should be controlled using the joint method when the three levers - RPM lever, throttle lever and turbocharger lever are moved together. However, in certain cases (for instance, when going higher than the critical altitude) the turbocharger lever should be adjusted separately. - It should be noted that turbocharger RPM changes relatively slowly and not immediately after the control lever adjustment. - The aircraft is equipped with the water injection system that boosts the power in the emergency mode. When this system is engaged, the exhaust back pressure and turbocharger RPM increase automatically while the mixture becomes leaner. The water supply is good for around 7 minutes at the emergency power. - The engine is equipped with an automatic fuel mixture control which maintains optimal mixture if the mixture lever is set to Auto Rich (85%25) position. To use automatic mixture leaning to reduce fuel consumption during flight it is necessary to set the mixture lever to Auto Lean (60%25) position. In the case of malfunction of the automatic mixture control the mixture lever should be set to Full Rich (100%25) position. To stop the engine mixture lever should be set to the Cut Off (0%25) position. - Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM. - Oil radiators shutters are manually operated. - The aircraft has trimmers for all flight-controls: pitch, roll and yaw. - Landing flaps have a hydraulic actuator and they can be extended to any angle up to 40°. - It is forbidden to open the cowl flaps at speeds exceeding 225 mph, perform sharp maneuvers with the opened cowl shutters and dive with the opened intercooler shutters. - The aircraft has a manual control for the tailwheel lock. The tailwheel should be locked when taxiing straight for a long distance and before takeoff and landing. - The aircraft has independent left and right hydraulic wheel brake controls. To apply either brake push the upper part of the rudder pedal. - The aircraft is equipped with a parking brake system. - The signal lamp lights up when the landing gear is up and the throttle is in the backward position or when the landing gear is down, but the throttle is in the forward position. - It should be noted that the aircraft requires a long takeoff run - around 650 meters at standard load and 1500 meters at maximum takeoff weight. It is possible to lower the flaps to 10-20 degrees to shorten the takeoff run. - The aircraft is equipped with one fuel gauge, but two indicator needles for the forward and rear fuel tanks. - The engine consumes much fuel at the combat power mode - around 4.5 gallons per minute. - The canopy has an emergency release system for bailouts. - The aircraft is equipped with the manual bomb release system for each of the three bomb racks. - The unguided rockets are launched using the electric controller which allows single, pair, triple and salvo (all rockets at 0.1 seconds interval) launch. - There is a backup mechanical sight which can be used if the main sight is damaged. Spitfire Mk.XIV Indicated stall speed in flight configuration: 152..172 km/h Indicated stall speed in takeoff/landing configuration: 145..163 km/h Dive speed limit: 756 km/h Maximum load factor: 12.5 G Stall angle of attack in flight configuration: 19.0 ° Stall angle of attack in landing configuration: 16.2 ° Maximum true air speed at sea level, 2750 RPM, boost +18: 574 km/h Maximum true air speed at 4000 m, 2750 RPM, boost +18: 671 km/h Maximum true air speed at 8100 m, 2750 RPM, boost +18: 720 km/h Service ceiling: 13400 m Climb rate at sea level: 23.8 m/s Climb rate at 2650 m: 23.5 m/s Climb rate at 6750 m: 18.2 m/s Maximum performance turn at sea level: 18.1 s, at 270 km/h IAS. Maximum performance turn at 3000 m: 21.0 s, at 260 km/h IAS. Flight endurance at 3000 m: 1 h 45 m, at 350 km/h IAS. Takeoff speed: 170..195 km/h Glideslope speed: 180..210 km/h Landing speed: 140..160 km/h Landing angle: 12.5 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates and turn times are given for 2750 RPM and boost +18. Engine: Model: Griffon 65 Maximum power in Take-off mode (2750 RPM, boost +12, low gear) at sea level: 1565 HP Maximum power in International power mode (2600 RPM, boost +9, low gear) at 4270 m: 1520 HP Maximum power in International power mode (2600 RPM, boost +9, high gear) at 8070 m: 1375 HP Maximum power in Emergency Max All Out mode (2750 RPM, boost +18, low gear) at 2134 m: 2063 HP Maximum power in Emergency Max All Out mode (2750 RPM, boost +18, high gear) at 6400 m: 1845 HP Engine modes: Max Cruising power (unlimited time): 2400 RPM, boost +7 International power (up to 1 hour): 2600 RPM, boost +9 Emergency Max All Out power (up to 5 minutes): 2750 RPM, boost +18 Water rated temperature in engine output: 105..115 °C Water maximum temperature in engine output: 135 °C Oil rated temperature in engine intake: 90 °C Oil maximum temperature in engine intake: 105 °C Supercharger gear shift altitude: automatic with possibility of manual switch to low gear Empty weight: 3295.0 kg Minimum weight (no ammo, 10%25 fuel): 3422.7 kg Standard weight: 3862.7 kg Fuel load: 363.3 kg / 504.6 l / 111 gallons Maximum useful load: 1027.8 kg Forward-firing armament ("c-type" wing): 2 x 20mm gun "Hispano Mk.II", 150 rounds per gun, 650 rounds per minute, wing-mounted 4 x 7.7mm machine gun "Browning .303", 350 rounds per gun, 1150 rounds per minute, wing-mounted Forward-firing armament ("e-type" wing): 2 x 20mm gun "Hispano Mk.II", 150 rounds per gun, 650 rounds per minute, wing-mounted 2 x 12.7mm machine gun "Browning .50", 250 rounds per gun, 850 rounds per minute, wing-mounted Bombs: 2 x 250 lb general purpose bomb "250 lb. G.P." 500 lb general purpose bomb "500 lb. G.P." Length: 9.9 m Wingspan: 11.21 m Wing surface: 22.48 m² Combat debut: January 1944 Additional airplane configurations list: 150 grade fuel(Allows +21 lb boost) Automatic supercharger gear shifting is disabled. Stages should be manually switched at 11000ft altitude. Estimated speed increase at sea level: 20 km/h 2 x 250 lb General Purpose Bomb Additional mass: 247 kg Ammunition mass: 227 kg Racks mass: 20 kg Estimated speed loss before drop: 22 km/h Estimated speed loss after drop: 11 km/h 500 lb General Purpose Bomb Additional mass: 237 kg Ammunition mass: 227 kg Racks mass: 10 kg Estimated speed loss before drop: 12 km/h Estimated speed loss after drop: 6 km/h 2 x 12.7mm "Browning .50" machine guns instead of 4 x 7.7mm "Browning .303" machine guns(E-type Wing) Additional mass: 48 kg Ammunition mass: 70 kg Gun mass: 72 kg Estimated speed gain: 5 km/h Rear view mirror Additional mass: 1 kg Estimated speed loss: 1 km/h MkII Gyro Gunsight Additional mass: 5.2 kg Estimated speed loss: 0 km/h Removal of wing-mounted machine guns to reduce total weight Removed mass: 95 kg Removed ammunition mass: 42 kg Removed guns mass: 53 kg Estimated speed gain: 8 km/h Clipped Wing Removed mass: 4 kg Estimated speed loss: 0 km/h Operation features: - Engine is equipped with the automatic governor of the manifold pressure that works when the throttle is set to 1/3 position or above. - Engine has a two stage mechanical supercharger which does not require manual control. It can be switched to the low gear manually. - Engine is equipped with an automatic fuel mixture control which maintains optimal mixture. - Engine RPM has an automatic governor that controls the propeller pitch to maintain the required RPM. - The water and oil radiators shutters are operated automatically, but there is a special manual mode that forces radiator shutters to open completely. - Aircraft has a neutral static stability. The elevator effectiveness is high, so the aircraft should be controlled carefully, not giving too much flight stick input. - Aircraft becomes unstable with extended landing flaps. - Aircraft is equipped with elevator and rudder trimmers. - Landing flaps have a pneumatic actuator so they can be extended to maximum position only. Speed with extended landing flaps is limited to 140 mph. - Airplane tail wheel rotates freely and does not have a lock. Since the landing gear wheels are relatively close to each other, it is necessary to confidently and accurately operate the rudder pedals during the takeoff and landing. - Airplane has differential pneumatic wheel brakes with shared control lever. This means that if the brake lever is held and the rudder pedal the opposite wheel brake is gradually released causing the plane to swing to one side or the other. - Airplane is equipped with a siren that warns a pilot if the throttle is set to low position with landing gear retracted. - It is impossible to open or close the canopy at high speed due to strong airflow. The canopy has an emergency release system for bailouts. - The aircraft is equipped with two underwing formation lights. - Standard gunsight is adjustable: both the target distance and target base can be set. - The gyroscopic gunsight automaticly calculates required angular deflection while firing at a target. It has 4 modes: fixed reticle, fixed and gyro reticle, gyro reticle, gyro reticle with the target range fixed at 150 yards (night mode). The angular deflection will be calculated correctly only if the target range is set properly. To set the range, adjust the target base first using separate controls and then set the range by adjusting the size of the rangefiding reticle to be the same as the target size. - Both gunsights have sliding sun-filters. Airplanes of "Flying Circus": SPAD 13.C1 Скрытый текст Engine V8 Hispano—Suiza 8Ba 220 hp Dimensions Height: 2600 mm Length: 6250 mm Wing span: 8080 mm Wing surface: 20,2 sq.m Weight Empty: 565 kg Takeoff: 820 kg Fuel capacity: 113,5 l Oil capacity: 17 l Climb rate 1000 m — 2 min. 32 sec. 2000 m — 5 min. 10 sec. 3000 m — 8 min. 24 sec. 4000 m — 12 min. 30 sec. 5000 m — 18 min. 01 sec. 6000 m — 26 min. 24 sec. 7000 m — 44 min. 24 sec. Maximum airspeed (IAS) sea level — 219 km/h 1000 m — 206 km/h 2000 m — 193 km/h 3000 m — 180 km/h 4000 m — 166 km/h 5000 m — 152 km/h 6000 m — 137 km/h 7000 m — 119 km/h Service ceiling 7000 m Endurance at 1000m nominal power (combat) — 1 h. 30 min. minimal consumption (cruise) — 3 h. Armament Forward firing: 2хVickers Mk.I 7.69mm, 400 rounds per barrel. Bomb load: 18 kg. Additional airplane configurations list: Скрытый текст Twin Vickers "Balloon" guns Ammo: 400 of 11.43mm rounds Projectile weight: 17,5 g Muzzle velocity: 610 m/s Guns weight: 26 kg Ammo weight: 32 kg Rate of fire: 600 rpm Total additional weight of weapon modification: 58 kg Aldis Refractor-type Collimator Sight (imported from Britain) Additional mass: 1 kg Le-Chretien Refractor-type Collimator Sight Additional mass: 1 kg Cockpit illumination lamp for night sorties Additional mass: 1 kg Two 24 lb bombs Additional mass: 25 kg Camera for taking aerial photographs Additional mass: 1 kg Story: The SPAD S.XIII was designed as an improved version of the SPAD S.VII. While appearing externally similar to its predecessor, it was in fact a completely new design. A second machine gun and more a powerful engine were fitted. In addition, an auxiliary fuel tank was placed in the central section of the upper wing. The main fuel tank had outlines of the lower fuselage section. To the left and behind the cockpit was an installation for a reconnaissance camera or a bomb load. The aircraft’s first flight was made on the 4th of April 1917. The plane was manufactured by Bleriot, Levasseur, Bernard, Kellner, Safca, Borel, and Nieuport. In all, 8472 planes of the type were built. The S.XIII first appeared at the front in late summer-early fall 1917, being initially supplied to French fighter squadrons. It was mainly used for engaging enemy planes, escorting bombers, aerial mapping, and recon; rarely was it used for the bombing of ground targets near the front lines. French pilots were eager to receive the S.XIII. The second machine gun provided increased firepower, and the new engine allowed it to fly and climb faster than its predecessors. Its controls remained effective even at high altitudes. The only remaining drawback, owing to its thin wing profile, was its decreased sensitivity of controls at low speeds, which often resulted in a stall. In a dive and level flight, the SPAD S.XIII was one of the fastest aircraft of its time. Pilots who flew it remarked, “It dives faster than the wind!” It participated in battles on all fronts during WWI. French, British, American and Italian units were all equipped with the type. S.E.5a Engine V8 Wolseley Viper 200 HP Dimensions Height: 2743 mm Length: 6300 mm Wing span: 8000 mm Wing surface: 23.7 sq.m Weight Empty: 635 kg Takeoff: 886 kg Fuel capacity: 148 l Oil capacity: 16 l Climb rate 1000 m — 2 min. 52 sec. 2000 m — 6 min. 15 sec. 3000 m — 10 min. 41 sec. 4000 m — 17 min. 03 sec. 5000 m — 28 min. 01 sec. Maximum airspeed (IAS) sea level — 223 km/h 1000 m — 209 km/h 2000 m — 194 km/h 3000 m — 180 km/h 4000 m — 165 km/h 5000 m — 150 km/h 6000 m — 133 km/h Service ceiling 5500 m Endurance at 1000 m nominal power (combat) — 2 h. 10 min. minimal consumption (cruise) — 6 h. 10 min. Armament Forward firing: Vickers Mk.I 7,69 mm, 400 rounds per barrel. Forward firing (wing mounted): Lewis 7,69 mm, 4 drums per 97 rounds each. Bomb load: 36 kg bomb. Additional airplane configurations list: Aldis Refractor-type Collimator Sight Additional mass: 2 kgNeedle Scale fuel level Gauge (0-30 Gallons) Additional mass: 1 kgCockpit illumination lamp for night sorties Additional mass: 1 kgUp to 4 x 11 kg (24 lb) Cooper General Purpose Bombs Additional mass: 56 kg Ammunition mass: 44 kg Racks mass: 12 kg Estimated speed loss before drop: 2 km/h Estimated speed loss after drop: 1 km/h Story: The S.E.5a (single-seat fighter, Scout Experimental 5a) was designed by the British company known as R.A.F. (Royal Aircraft Factory). The goal was to build a fighter around the 200hp Hispano-Suiza engine, which would make it to be fast and have a high climbing speed. To achieve this goal, engineers had to settle on a compromise. By making the wing profile thin, they simultaneously increased its surface area. This design featured ailerons in both the upper and lower wings. In total, 5269 planes were built by the end of the war. The plane’s first trial flight was performed in January 1917, and it saw action in June 1917 at the British No. 56 Squadron RFC. It was used to engage enemy fighters and balloons and to escort bombers; only rarely was it used to engage ground targets near the front lines. In evaluating the aircraft, pilots mentioned its structural durability, sufficient manoeuvrability, stability in dives and when firing machine guns, fine handling, and good sensitivity of controls at low speeds. When landing at high speed, the plane could not touch down due to its high wing lift. It is notable that most of the top British aces flew this type of plane. It was even given a nickname - “ace-maker.” During the aircraft’s service, the poor reliability of the Hispano-Suiza engine became apparent; as a result, the plane was also fitted with the more reliable Wolseley Viper engine (license-built by the British Hispano-Suiza factories). The landing gear structure had to be redesigned after frequent reports were made of it breaking upon landing. This involved changing its shape (metal welded tubes were replaced by a wooden frame). The aircraft participated in battles in Europe on the Western Front and in Macedonia and also in Mesopotamia and Palestine. Sopwith Camel Скрытый текст Engine Clerget 9B rotary 9 cyl., 130 h.p. Dimensions Height : 2590 mm Length : 5490 mm Wing span : 8530 mm Wing surface: 21,46 sq.m. Weight Empty weight : 431 kg Takeoff weight : 700 kg Fuel capacity : 168 l Oil capacity : 20 l Climb rate 1000 m — 2 min. 37 sec 2000 m — 5 min. 46 sec. 3000 m — 9 min. 40 sec. 4000 m — 14 min. 45 sec. 5000 m — 21 min. 41 sec. 6000 m — 32 min. 17 sec. Maximum airspeed (IAS) sea level — 195 km/h 1000 m — 183 km/h 2000 m — 170 km/h 3000 m — 158 km/h 4000 m — 145 km/h 5000 m — 132 km/h 6000 m — 117 km/h Service ceiling 6700 m Endurance at 1000m nominal power (combat) — 2 h. 50 min. minimal consumption (cruise) — 5 h. Armament: Forward firing: 2хVickers Mk.I 7.69, 500 rounds per barrel. Bomboad: 36kg Additional airplane configurations list: Скрытый текст Aldis Refractor-type Collimator Sight (imported from Britain) Additional mass: 1 kg Enlarged cutout in the upper wing for improved field of view. Estimated speed loss: 2 km/h Cockpit illumination lamp for night sorties Additional mass: 1 kg Story: The Sopwith Camel's construction was based on that of its predecessor, the Sopwith Pup. Sopwith's chief designer Herbert Smith decided to somewhat alter the Pup’s design, since a newarger and heavier engine would have to be mounted. Some changes were made to theanding gear struts, the spacing of the wings and stabiliser were increased, and the fuselage acquired an extension to the cockpit's trailing edge, whichooked ratherike a camel’s hump. That 'hump' is what gave the plane its name - the Sopwith Camel. A remarkable detail of the plane’s construction was its compactness: the pilot’s seat, fuel tanks, machine guns and engine were all installed very close together. In parallel with the work of the main Sopwith factory, the plane was also assembled by a number of other companies such as Ruston Proctor Co, Portholme Aerodrome Ltd, Boulton & Paul Ltd, British Caudron Co. Ltd, Clayton & Shuttleworth Ltd, Hooper & Co. Ltd and others. In total, about 5490 Camels were built. The Camel’s first flight trials were performed by the British No. 60 squadron in March of 1917, which were followed by a series of minor improvements to the plane’s construction. Production aircraft were first delivered to fighter squadrons in May of 1917. It was primarily used for destroying enemy aircraft and balloons, while from time to time it was also engaged in ground attack operations. English journalists referred to this plane as a “small and agile beast.” Camel pilots mentioned the plane’s well-balanced flight controls, the good upward view, and the high cruising speed. Due to the aircraft's unique balance, the plane could almost instantly change its heading, which made the Camel a dangerous opponent. The typical combat scenario for the Camel pilot was a dogfight at low and medium altitudes, where the Camel had the advantage in steep turns. Veterans were known to say, “Once you become a Camel pilot, you will fly it forever.” In addition to equipping British units, this plane was also piloted by four American squadrons of the U.S. Air Service and by some Belgian pilots. Sopwith Dolphin Engine V8 Hispano—Suiza 8Ba 200 hp Dimensions Height: 2600 mm Length: 6700 mm Wing span: 10000 mm Wing surface: 24,5 sq.m Weight Empty: 660 kg Takeoff: 893 kg Fuel capacity: 123 l Oil capacity: 18 l Climb rate 1000 m — 2 min. 44 sec. 2000 m — 5 min. 48 sec. 3000 m — 9 min. 32 sec. 4000 m — 14 min. 14 sec. 5000 m — 20 min. 30 sec. 6000 m — 29 min. 42 sec. 7000 m — 47 min. 04 sec. Maximum airspeed sea level — 203 km/h 1000 m — 192 km/h 2000 m — 182 km/h 3000 m — 171 km/h 4000 m — 160 km/h 5000 m — 148 km/h 6000 m — 134 km/h 7000 m — 116 km/h Service ceiling 7100 m Endurance at 1000 m nominal power (combat) — 1 h. 40 min. minimal consumption (cruise) — 3 h. 20 min. Armament Forward firing: 2 х Vickers Mk.I 7.69mm, 500 rounds per barrel. Bomb load: 36 kg Additional airplane configurations list: Two overwing mounted additional Lewis machineguns with changeable position. Ammo: 388 of 7.69mm rounds (4 drums with 97 rounds in each) Forward position: 25° Upward position: 45° Projectile weight: 11 g Muzzle velocity: 745 m/s Rate of fire: 550 rpm Guns weight: 15 kg (w/o ammo drum) Mounts weight: 2 kg Ammo weight: 16 kg Total weight: 33 kg Estimated speed loss: 7-18 km/hTwo additional lower-wing mounted fixed Lewis machine guns. Ammo: 194 of 7.69mm rounds (2 drums with 97 rounds in each) Projectile weight: 11 g Muzzle velocity: 745 m/s Rate of fire: 550 rpm Guns weight: 15 kg (w/o ammo drum) Mounts weight: 2 kg Ammo weight: 8 kg Total weight: 25 kg Estimated speed loss: 3 km/hAldis Refractor-type Collimator Sight Additional mass: 2 kgO.S.I.C engine coolant temperature Indicator (30-100 °C) Additional mass: 1 kgCockpit illumination lamp for night sorties Additional mass: 1 kgUp to 4 x 11 kg (24 lb) Cooper General Purpose Bombs Additional mass: 56 kg Ammunition mass: 44 kg Racks mass: 12 kg Estimated speed loss before drop: 2 km/h Estimated speed loss after drop: 1 km/h Story: The Sopwith Dolphin was designed by the Sopwith Aviation Company in Britain. In designing the aircraft, the flaws of the Sopwith Camel were taken into account. These included bad forward and upward visibility and difficulties of handling a rotary-powered plane. In response to the latter issue, the engineers elected to fit the new aircraft with an inline engine. The design featured a compact arrangement of the cockpit, fuel tanks, machine guns and engine. This resulted in the pilot’s head being level with the hatch on the upper wing. The radiators were moved to the sides of the fuselage and behind the cockpit. The first trial flights were made in May 1917. In addition to the Sopwith Aviation Company, several other companies manufactured the aircraft: Darracq, Hooper, and SACA. By the end of the war, 1532 planes of the type had been built. Operational evaluation of the Dolphin began with the British No. 56 Squadron on June 13, 1917. Several design improvements would follow. In January 1918, No. 19 Squadron became the first operational unit to receive production examples of the Dolphin. The type was employed against enemy fighters and balloons, especially at high altitudes, where it was superior to the Sopwith Camel. It was also used to bomb and strafe ground targets. Dolphin pilots noted the plane’s good balance of controls, perfect visibility upward and forward, but the downward visibility was obscured by the lower wings and the engine cowling. The plane was a formidable opponent, as it possessed the manoeuvrability of the Sopwith Camel and a speed and climb rate equal to that of the S.E.5a. Pilots often complained about the cockpit crumpling and its tendency to nose over on harsh landings. For a short period, French and American pilots flew these aircraft. It took part in battles over the Western Front. Bristol F2B (F.II / F.III) Engine V-type 12 cyl. Rolls Royce Falcon II / Falcon III Power: 255 hp (2000 RPM) / 285 hp (2200 RPM) Dimensions: Height: 2970 mm Length: 7874 mm Wing span: 11986 mm Wing surface: 37.7 sq.m Weight: Empty: 885 kg Crew: 160 kg Fuel capacity: 170.5 liters (127 kg) Oil capacity: 15.2 liters (14 kg) Takeoff without bombload: 1262 kg Takeoff with 4 x 112 lb (203 kg) bombs: 1465 kg Takeoff with 12 x 24 lb (131 kg) bombs: 1393 kg Speed (IAS), without bombload: seal level - 192 km/h / 198 km/h 1000 - 180 km/h / 186 km/h 2000 - 168 km/h / 174 km/h 3000 - 155 km/h / 162 km/h 4000 - 142 km/h / 150 km/h 5000 - 128 km/h / 137 km/h 6000 - 106 km/h / 123 km/h Climb rate, full fuel load, no bombs: 1000 m - 3 min. 18 sec. / 2 min. 57 sec. 2000 m - 7 min. 20 sec. / 6 min. 24 sec. 3000 m - 12 min. 42 sec. / 10 min. 49 sec. 4000 m - 20 min. 41 sec. / 16 min. 50 sec. 5000 m - 35 min. 54 sec. / 26 min. 10 sec. Service ceiling: 5200 m / 5900 m Theoretical ceiling: 6100 m / 6900 m Endurance at 1000 m: nominal power (combat) — 1 h. 50 min. minimal consumption — 4 h. 50 min. / 5 h. 10 min. Armament: Forward firing: 1 x Vickers Mk.I 7.69 mm, 973 rounds per barrel Tail upper position: 2 x Lewis 7.69 mm, 8 drums with 97 rounds each 1749 7.69 mm rounds in total Bomb load variations: 12 x 24 lb (131 kg) 8 x 24 lb + 2 x 112lb (187 kg) 4 x 112 lb (203 kg) 2 x 112 lb (102 kg) 203 kg in total Additional airplane configurations list: Two overwing mounted additional Lewis machineguns with changeable position. Ammo: 582 of 7.69mm rounds (6 drums with 97 rounds in each) Forward position: 0° Upward position: 62° Projectile weight: 11 g Muzzle velocity: 745 m/s Rate of fire: 550 rpm Guns weight: 15 kg (w/o ammo drums) Mounts weight: 8 kg Ammo weight: 24 kg Total weight: 47 kg Estimated speed loss: 4-14 km/hScarff ring turret with twin Lewis MG Ammo: 776 of 7.69mm rounds (8 drums with 97 rounds in each) Projectile weight: 11 g Muzzle velocity: 745 m/s Rate of fire: 550 rpm Guns weight: 15 kg (w/o ammo drums) Mount weight: 12 kg Ammo weight: 32 kg Total weight: 59 kg Estimated speed loss: 2 km/hAldis Refractor-type Collimator Sight Additional mass: 2 kgNeedle Scale fuel level Gauge (0-30 Gallons) Additional mass: 1 kgCockpit illumination lamp for night sorties Additional mass: 1 kgCooper / H.E.R.L. bombsUp to 12 x 11 kg (24 lb) General Purpose Bombs Additional mass: 167 kg Ammunition mass: 131 kg Racks mass: 36 kg Estimated speed loss before drop: 7 km/h Estimated speed loss after drop: 3 km/hUp to 4 x 51 kg (112 lb) H.E.R.L. General Purpose Bombs Additional mass: 252 kg Ammunition mass: 204 kg Racks mass: 48 kg Estimated speed loss before drop: 8 km/h Estimated speed loss after drop: 4 km/hCamera for taking aerial photographs Additional mass: 10 kgRadio transmitter Additional mass: 10 kg Story: Design of the Bristol started in March of 1916 as an intended replacement for the B.E. two seater Series. It was designed as a reconnaissance aircraft, but additionally the new type was also going to have to be capable of carrying out scout patrols. It was supplied with dual controls, wireless radio, camera equipment and armed with a fixed Vickers gun firing through the cowling and a rear turret with one or two Lewis guns. The first prototype Bristol F.2A flew in September of 1916, equipped with a Rolls Royce Mk.1 engine. After successful trials, the aircraft went into production. The first combat unit equipped with Bristols to arrive in France was No.48 Squadron, which arrived at the front on March 8, 1917. The first offensive patrol was flown on April 5, 1917, but proved to be a disastrous debut for the Bristol. The patrol consisted of six F.2As and was led by Captain I.V. Leefe-Robinson, V.C. When over Douai, they were attacked by five Albatros D.IIIs led by Manfred von Richthofen, who shot down two of the Bristols for his thirty-fifth and thirty-sixth victories. Two other Bristols, one of them flown by Leefe-Robinson himself, were also accounted for by Richthofen\'s pilots. This failure happened mostly due to old tactics used by the first Bristol pilots - as they used it to fly in close formation and only with defensive tactics. But later, as pilots gained combat experience, the Bristol proved to be a superior combat machine when used as a fighter plane. Later on, some changes were made to the Bristol airframe, and it was also supplied with new Falcon II and Falcon III engines, whereupon it was re-designated as the Bristol F.2B and became one of the best, if not the best, two seat fighter of the Great War. Due to a shortage of the Rolls Royce Falcon engine, a wide variety of engines were installed, such as 300hp Hispano, Raf 4a, Sunbeam Arab and Liberty engines. Fast, with a good climb rate, rugged, very fast in dives and flown by aggressive and experienced pilots, Bristols soon became feared by enemy opponents. Usually, German pilots chose to evade Bristols if the Germans did not have superior numbers. The most successful Bristol ace who flew F.2Bs as a pilot, Andrew Edward McKeever from No.11 squadron, scored an impressive 31 kills flying Bristols. However, his record was overshadowed by that of the highest scoring observer ace of the war, Charles George Gass, who scored 39 (!!!) kills while flying as a Bristol gunner! While excelling as a fighter, the Bristol was also capable of being a good ground attack aircraft. It could carry up to 450 lbs of bombs on external racks. Some of the Bristols were also equipped with a Negative Lens bombsight. Being a very successful aircraft, Bristol Fighters were used by RAF squadrons through the 1920s. A total of 3,101 Bristol Fighters were produced up until the end of 1918. Albatros D.Va Engine 6—cyl. inline Mercedes D. IIIa 180 HP Dimensions Height: 2700 mm Length: 7330 mm Wing span: 9050 mm Wing surface: 21.2 sq.m Weight Empty: 680 kg Takeoff: 915 kg Fuel capacity: 103 l Oil capacity: 9 l Climb rate 1000 m — 3 min. 58 sec. 2000 m — 8 min. 33 sec. 3000 m — 14 min. 22 sec. 4000 m — 22 min. 29 sec. 5000 m — 36 min. 41 sec. Maximum airspeed (IAS) sea level — 169 km/h 1000 m — 161 km/h 2000 m — 153 km/h 3000 m — 145 km/h 4000 m — 136 km/h 5000 m — 125 km/h 6000 m — 109 km/h Service ceiling 5400 m Endurance at 1000 m nominal power (combat) — 1 h. 40 min. minimal consumption (cruise) — 4 h. 20 min. Forward firing armament: 2 x LMG 08/15 Spandau 7.92mm, 500 rounds per barrel Additional airplane configurations list: Oigee Reflector-type Collimator sight (with removable daytime dimmer) Additional mass: 2 kgAdditional sight with front sight and rear sight mountings Additional mass: 1 kgAnemometer, Altimeter, Clock Wilhelm Morell Anemometer (45-250 km/h) D.R.P Altimeter (0-8000 m) Additional mass: 2 kgD.R.G.M liquid Inclinometer (indicates bank while on ground and sideslip while in flight) Additional mass: 1 kgWilhelm Morell needle scale Bullet Counters for 2 machine guns Additional mass: 1 kgA.Schlegelmilch engine coolant temperature indicator (0-100 °C) Additional mass: 1 kgCockpit illumination lamp for night sorties Additional mass: 1 kgCockpit mounted additional Lewis machinegun with changeable position. Ammo: 291 of 7.69mm rounds (3 drums with 97 rounds in each) Forward position: 8° Upward position: 45° Projectile weight: 11 g Muzzle velocity: 745 m/s Rate of fire: 550 rpm Gun weight: 7 kg (w/o ammo drum) Mount weight: 4 kg Ammo weight: 12 kg Total weight: 23 kg Estimated speed loss: 2-6 km/h Story: The engineers of Albatros Werke faced the task of building a fast and manoeuvrable fighter plane. The older Albatros D.III had a lower wing defect that led to failure of the wing in a steep dive. Having been unable to find out the reason of these failures, the engineers moved the aileron control wires from the lower wing to the top wing. Test flights were carried out in the spring of 1917. Externally, the Albatros D.V differed from earlier Albatros models: it had a larger tail fin surface; the top wing was lowered closer to the fuselage; the radiator was set to starboard of the centreline, and the fuselage was more rounded. Fighter squadrons began receiving the Albatros D.V in May 1917. Several months of combat experience showed that the lower wing problem had not been solved. In response, the engineers moved the aileron control wires back to the lower wing and strengthened the attachment point of the V-shaped strut to the lower spar with an additional strut. In addition, the more powerful Mercedes D.IIIa engine was installed. The updated plane was called the Albatros D.Va. Total of 1650 Albatros D.V and D.Va aircraft were built at Albatros Werke and Ostdeutsche Albatros Werke. The Albatros D.Va was mainly used against enemy aircraft. Pilots noted great visibility, handling, sufficient speed and rate of climb. The new engine improved the aircraft’s high altitude flight characteristics. However, pilots had no confidence in the new low wing attachment and refused to perform steep dives in combat. Despite this, veteran pilots continued to increase their combat scores, and employing large numbers of the aircraft in sorties became more frequent. This model participated in battles on the Western Front and the Palestinian Front. Fokker Dr.I Скрытый текст Engine Oberursel UR II rotary 9 cyl. 110 hp Dimensions Height: 2950 mm Length: 5770 mm Wing span: 7190 mm Wing surface: 18,66 sq.m. Weight Empty weight: 388 kg Takeoff weight: 571 kg Fuel capacity: 72 l Oil capacity: 20 l Climb rate 1000 m — 3 min. 15 sec. 2000 m — 6 min. 38 sec. 3000 m — 10 min. 35 sec. 4000 m — 15 min. 20 sec. 5000 m — 21 min. 17 sec. 6000 m — 29 min. 09 sec. 7000 m — 40 min. 55 sec. 8000 m — 64 min. 33 sec. Maximum airspeed (IAS) sea level — 169: km/h 1000 m — 161 km/h 2000 m — 153 km/h 3000 m — 144 km/h 4000 m — 136 km/h 5000 m — 127 km/h 6000 m — 118 km/h 7000 m — 108 km/h 8000 m — 94 km/h Service ceiling 7900 m Endurance(h.,min.) at 1000m nominal power (combat) — 1 h. 40 min. minimal consumption (cruise) — 2 h. 30 min Armament Forward firing: 2xLMG 08/15 Spandau 7.92mm, 500 rounds per barrel Additional airplane configurations list: Скрытый текст Oigee Reflector-type Collimator sight (daytime dimmer installed) Additional mass: 1 kg Oigee Reflector-type Collimator sight (daytime dimmer removed) Additional mass: 1 kg Additional sight with front sight and rear sight mountings Additional mass: 1 kg D.R.G.M liquid Inclinometer (indicates bank while on ground and sideslip while in flight) Additional mass: 1 kg Wilhelm Morell needle scale Bullet Counters for 2 machine guns Additional mass: 1 kg Cockpit illumination lamp for night sorties Additional mass: 1 kg Story: In the spring of 1917, during a visit to Jasta 11, Anthony Fokker inspected the construction of a captured British fighter, the Sopwith Triplane. Manfred von Richthofen related to Fokker the details of his dogfight with this new aeroplane. It was only due to his great experience that the Red Baron managed to avoid defeat. The prototype of the F.I (the name at the time of the Dr.I) triplane was made ready by August 1917. Some remarkable details of its construction were as follows: a steel tube fuselage frame, as well as metal frames for the stabilizer and tail fin; an absence of bracing trusses; and the placement of the ailerons on the upper wing. The plane was more compact and robust than the British Sopwith Triplane. In total, 320 Dr.I triplanes were built. On the 23rd of September 1917, Werner Voss shot down two British fighters while piloting an experimental version of the plane. Soon afterwards, he was attacked by six SE5s of the Royal Flying Corps. Each British plane was damaged in the course of this dramatic and historic fight, which forced two of their number to retire from the battle. It was only because he was outnumbered that the ace Voss unfortunately lost his life. By October 1917, the first production Fokker Dr.I planes were being delivered to fighter squadrons. The Fokker Dr.I triplane was a superb fighter, but it was rarely used to cover two-seater recon planes. Dr.I pilots reported an excellent rate of climb and manoeuvrability and a good view from the cockpit. Pilots reported, "You need only a light touch to swing this plane around!” Thanks to these features, the triplane pilot could decide whether to disengage from an attacking enemy or to attack an enemy plane. It could engage on even terms the king of the dogfight, the British Sopwith Camel, with a good chance of victory. RFC pilots were especially apprehensive of situations where the Fokker Dr.I and the Albatros D.Va were flying together in combat formation. The Fokkers would initiate the dogfight and the Albatros pilots would shoot down enemy planes attempting to disengage and leave the battle. By the spring of 1918, the plane was obsolete. Only the most outstanding German aces, masterfully piloting the plane and sharpshooting their enemies, continued to fly the triplane in combat. Fokker D.VII Engine 6 cyl. inline Mercedes D.IIIa 180 hp Dimensions Height: 2950 mm Length: 6950 mm Wing span: 8700 mm Wing surface: 20,4 sq.m Weight Empty: 700 kg Takeoff: 909 kg Fuel capacity: 91 l Oil capacity: 11 l Climb rate 1000 m — 3 min. 02 sec. 2000 m — 6 min. 31 sec. 3000 m — 10 min. 54 sec. 4000 m — 16 min. 50 sec. 5000 m — 26 min. 21 sec. Maximum airspeed (IAS) sea level — 194 km/h 1000 m — 184 km/h 2000 m — 172 km/h 3000 m — 160 km/h 4000 m — 146 km/h 5000 m — 130 km/h Service ceiling 5700 m Endurance at 1000 m nominal power (combat) - 1 h. 25 min. minimal consumption (cruise) - 2 h. 50 min. Armament Forward firing: 2хLMG 08/15 Spandau 7,92mm, 500 rounds per barrel. Additional airplane configurations list: Oigee Reflector-type Collimator sight (with removable daytime dimmer) Additional mass: 2 kgAdditional sight with front sight and rear sight mountings Additional mass: 1 kgWilhelm Morell Anemometer (45-250 km/h) Additional mass: 1 kgD.R.P Altimeter (0-8000 m) Additional mass: 1 kgWilhelm Morell digital bullet counters for 2 machine guns Additional mass: 1 kgA.Schlegelmilch engine coolant temperature indicator (0-100 °C) Additional mass: 1 kgCockpit illumination lamp for night sorties Additional mass: 1 kgCockpit mounted additional Lewis machinegun with changeable position. Ammo: 291 of 7.69mm rounds (3 drums with 97 rounds in each) Forward position: 8° Upward position: 45° Projectile weight: 11 g Muzzle velocity: 745 m/s Rate of fire: 550 rpm Gun weight: 7 kg (w/o ammo drum) Mount weight: 4 kg Ammo weight: 12 kg Total weight: 23 kg Estimated speed loss: 2-6 km/h Story: The Fokker D.VII was designed by Reinhold Platz of the Fokker-Flugzeugwerke. His task was to create a fighter capable of beating the French SPAD XIII and British S.E.5a fighters. Some notable design features of the type included a metal airframe structure, a thick-sectioned wing, and a lack of bracing wires. A competition among various new fighters took place in Adlershof from January 21st to February 12th, 1918, during the course of which the D.VII prototype proved to be the fastest, most durable, and the best-climbing aircraft. Manfred von Richthofen, a close friend of Anthony Fokker, also evaluated the prototype and noted some minor flaws. In particular, he noted the aircraft exhibited instability in a long dive, which was later corrected. The success of the design led to it being produced at a number of factories, including Fokker Flugzeugwerke, Albatros Werke, and the Ostdeutsche Albatros Werke. The Fokker D.VII would become one of the best - if not ultimately the best - fighter by the end of the war. In total, 2029 planes were produced and sent to the front by the end of 1918. The first production aircraft reached the frontline airfields of Bavarian squadrons in April 1918. The Fokker D.VII was used to escort bombers, engage enemy fighters, and attack balloons; it was rarely used for strafing enemy supply columns in the immediate battle area and for recon. During its initial service, it became clear that the water-cooled radiator did not cool the engine sufficiently. The problem was fixed by modifying the radiator facing, engine cowling, and by increasing the airflow through the cylinders. D.VII pilots noted the type’s good climb speed, excellent cockpit visibility, stability in manoeuvres, and good handling at low speeds. Pilots excitedly exclaimed, "The plane is like hanging on its propeller!" All of these attributes helped pilots in carrying out offensive and defensive missions. German squadrons equipped with this type were the main opponents of Allied aviation until the war’s end. Fokker D.VIIF Engine 6 cyl. inline BMW IIIa 232 hp Dimensions Height: 2950 mm Length: 6950 mm Wing span: 8700 mm Wing surface: 20,4 sq.m Weight Empty: 669,5 kg Takeoff: 904 kg Fuel capacity: 95 l Oil capacity: 20,7 l Climb rate 1000 m — 2 min. 18 sec. 2000 m — 4 min. 40 sec. 3000 m — 7 min. 11 sec. 4000 m — 9 min. 47 sec. 5000 m — 12 min. 42 sec. 6000 m — 16 min. 23 sec. 7000 m — 21 min. 19 sec. 8000 m — 28 min. 59 sec. Maximum airspeed (IAS) sea level — 197 km/h 1000 m — 192 km/h 2000 m — 184 km/h 3000 m — 181 km/h 4000 m — 176 km/h 5000 m — 165 km/h 6000 m — 153 km/h 7000 m — 140 km/h 8000 m — 126 km/h 9000 m — 106 km/h Service ceiling ~9000 m Endurance at 1000 m nominal power (combat) - 1 h. 50 min. minimal consumption (cruise) - 5 h. 30 min. Armament Forward firing: 2хLMG 08/15 Spandau 7,92mm, 500 rounds per barrel. Additional airplane configurations list: Oigee Reflector-type Collimator sight (with removable daytime dimmer) Additional mass: 2 kgAdditional sight with front sight and rear sight mountings Additional mass: 1 kgWilhelm Morell Anemometer (45-250 km/h) Additional mass: 1 kgD.R.P Altimeter (0-8000 m) Additional mass: 1 kgA.Schlegelmilch engine coolant temperature indicator (0-100 °C) Additional mass: 1 kgCockpit illumination lamp for night sorties Additional mass: 1 kgCockpit mounted additional Lewis machinegun with changeable position. Ammo: 291 of 7.69mm rounds (3 drums with 97 rounds in each) Forward position: 8° Upward position: 45° Projectile weight: 11 g Muzzle velocity: 745 m/s Rate of fire: 550 rpm Gun weight: 7 kg (w/o ammo drum) Mount weight: 4 kg Ammo weight: 12 kg Total weight: 23 kg Estimated speed loss: 2-6 km/h Story: The Fokker D.VII was designed by Reinhold Platz of the Fokker-Flugzeugwerke. His task was to create a fighter capable of beating the French SPAD XIII and British S.E.5a fighters. Some notable design features of the type included a metal airframe structure, a thick-sectioned wing, and a lack of bracing wires. A competition among various new fighters took place in Adlershof from January 21st to February 12th, 1918, during the course of which the D.VII prototype proved to be the fastest, most durable, and the best-climbing aircraft. Manfred von Richthofen, a close friend of Anthony Fokker, also evaluated the prototype and noted some minor flaws. In particular, he noted the aircraft exhibited instability in a long dive, which was later corrected. The success of the design led to it being produced at a number of factories, including Fokker Flugzeugwerke, Albatros Werke, and the Ostdeutsche Albatros Werke. The Fokker D.VII would become one of the best - if not ultimately the best - fighter by the end of the war. In total, 2029 planes were produced and sent to the front by the end of 1918. The first production aircraft reached the frontline airfields of Bavarian squadrons in April 1918. The Fokker D.VII was used to escort bombers, engage enemy fighters, and attack balloons; it was rarely used for strafing enemy supply columns in the immediate battle area and for recon. During its initial service, it became clear that the water-cooled radiator did not cool the engine sufficiently. The problem was fixed by modifying the radiator facing, engine cowling, and by increasing the airflow through the cylinders. D.VII pilots noted the type’s good climb speed, excellent cockpit visibility, stability in manoeuvres, and good handling at low speeds. Pilots excitedly exclaimed, "The plane is like hanging on its propeller!" All of these attributes helped pilots in carrying out offensive and defensive missions. German squadrons equipped with this type were the main opponents of Allied aviation until the war’s end. The Fokker D.VII was generally equipped with the Mercedes D.IIIa engine, but a new BMW engine type with the D.VIIF designation was also fitted. This new high compression BMW engine with high altitude control gave the D.VII much better performance. Its climb rate was almost twice that as the Mercedes-equipped version, and when flown at maximum throttle the engine was capable of generating almost 250 horsepower at ground level for a short time. With a nominal rating of 230 horsepower and a newly designed carburettor, this engine very much improved the aircraft's high altitude performance and pushed the aircraft’s performance to a new level. However, there was a persistent shortage of BMW engines, and as a result, only every third or fourth aircraft had this type of engine installed. This BMW IIIa engine had a special control lever - "Höhengashebel" - which was used to gain more power at higher altitudes. Engaging it at lower altitudes could lead to engine malfunction (detonation). The D.VIIF was mainly supplied to the best and most proven frontline squadrons. As a result, the best German pilots were now able to outclass the latest Allied aircraft types in a plane superior to those of the Allies in almost every important aspect. Pfalz D.IIIa Скрытый текст Engine Inline 6 cyl. Mercedes D.IIIa, 180 hp Dimensions Height: 2670 mm Length: 6950 mm Wing span: 9400 mm Wing surface: 22,09 sq.m Weight Empty: 725 Takeoff: 905 Fuel capacity: 94 l Oil capacity: 20 l Climb rate 1000 m — 3 min. 23 sec. 2000 m — 7 min. 19 sec. 3000 m — 12 min. 02 sec. 4000 m — 18 min. 01 sec. 5000 m — 26 min. 22 sec. 6000 m — 40 min. 53 sec. Maximum airspeed (IAS) sea level — 171 km/h 1000 m — 164 km/h 2000 m — 155 km/h 3000 m — 147 km/h 4000 m — 138 km/h 5000 m — 127 km/h 6000 m — 114 km/h Service ceiling 6100 m Endurance at 1000m nominal power (combat) — 1 h. 30 min. minimal consumption (cruise) — 2 h. 50 min. Armament Forward firing: 2хLMG 08/15 Spandau 7,92mm, 500 rounds per barrel. Additional airplane configurations list: Скрытый текст Oigee Reflector-type Collimator sight (daytime dimmer installed) Additional mass: 1 kg Oigee Reflector-type Collimator sight (daytime dimmer removed) Additional mass: 1 kg Additional sight with front sight and rear sight mountings Additional mass: 1 kg Wilhelm Morell Anemometer (45-250 km/h) Additional mass: 1 kg D.R.G.M liquid Inclinometer (indicates bank while on ground and sideslip while in flight) Additional mass: 1 kg D.R.P Altimeter (0-8000 m) Additional mass: 1 kg Wilhelm Morell needle scale Bullet Counters for 2 machine guns Additional mass: 1 kg A.Schlegelmilch engine coolant temperature indicator (0-100 °C) Additional mass: 1 kg Cockpit illumination lamp for night sorties Additional mass: 1 kg Story: The Pfalz D.III was designed by Pfalz Flugzeugwerke. German engineers were impressed by the famous French Nieuport fighters, which were designed with “one-and-a-half” wings. As such, Pfalz’s design was based on the achievements of French engineers. The first trial flight was carried out in May 1917. The plane’s design featured machine guns mounted on the sides of the engine and aileron control wires situated in the lower wing. Half a year later, the Pfalz D.IIIa was introduced. It featured a more powerful engine, a larger tail fin, a modified shape of the lower wing and machine guns mounted at the pilot's line of sight. In all, 1010 Pfalz D.III and Pfalz D.IIIa aircraft were built. In June 1917, the first Pfalz D.IIIs entered service with combat squadrons. The plane was used for bomber escort and for engaging enemy fighters and balloons. Pilots noted its exceptional cockpit visibility, good manoeuvrability, and stability when firing the machine guns; speed and climb rate were described as good. Some pilots claimed that its control sensitivity was even better than that of the Albatros D.V. Its structural durability permitted steep dives in combat and successful forced landings. English and French pilots claimed that one could shoot it down only when seriously wounding or killing the pilot. Its flight characteristics improved slightly when the Mercedes D.IIIa engine was fitted. The plane participated in battles over the Western and the Turkish fronts. Halberstadt CL.II (180 h.p. / 200 h.p.) Engine 6—cyl. inline Mercedes D.IIIa / Mercedes D.IIIaü Power: 180 hp / 200 hp Dimensions: Height: 2750 mm Length: 7300 mm Wing span: 10770 mm Wing surface: 27.5 sq.m Weight: Empty: 735 kg Crew: 160 kg Fuel capacity: 155 liters (115 kg) Oil capacity: 28 liters (22 kg) Takeoff without bombload: 1032 kg Takeoff with 3 x 50 kg bombs: 1182 kg Takeoff with 12 x 12,5 kg bombs: 1182 kg Speed (IAS), without bombload: seal level - 166 km/h / 174 km/h 1000 - 156 km/h / 164 km/h 2000 - 146 km/h / 154 km/h 3000 - 135 km/h / 144 km/h 4000 - 122 km/h / 132 km/h 5000 - 106 km/h / 120 km/h 6000 - --- km/h / 100 km/h Climb rate, full fuel load, no bombs: 1000 m - 5 min. 33 sec. / 4 min. 20 sec. 2000 m - 12 min. 44 sec. / 9 min. 38 sec. 3000 m - 23 min. 14 sec. / 16 min. 44 sec. 4000 m - 42 min. 40 sec. / 27 min. 27 sec. Service ceiling: 4100 m / 4900 m Theoretical ceiling: 5300 m / 6100 m Endurance at 1000 m: nominal power (combat) — 3 h. 10 min. minimal consumption — 6 h. / 6 h. 40 min. Armament: Forward firing: 1 х LMG 08/15 Spandau 7,92 mm, 500 rounds Turret: 1 х LMG 14/17 Parabellum 7,92 mm, 3 boxes with 250 rounds each. Bomb load variations: 12 x 12.5 kg (150 kg) 1 x 50 kg + 8 x 12.5 kg (150 kg) 3 x 50 kg (150 kg) 4 x 12.5 kg (50 kg) 1 x 50 kg (50 kg) 150 kg in total. Additional airplane configurations list: Twin fixed forward firing LMG 08/15 guns. Ammo: 1000 of 7.92mm rounds (500 rounds for each gun) Projectile weight: 10 g Muzzle velocity: 825 m/s Rate of fire: 650 rpm Guns weight: 26 kg Mount weight: 8 kg Ammo weight: 20 kg Total weight: 54 kg Estimated speed loss: 4 km/hRing turret with twin Parabellum machine guns. Ammo: 1500 of 7.92mm rounds (6 drums with 250 rounds in each) Projectile weight: 10 g Muzzle velocity: 825 m/s Rate of fire: 700 rpm Guns weight: 19 kg (w/o ammo drums) Mount weight: 5 kg Ammo weight: 30 kg Total weight: 54 kg Estimated speed loss: 8 km/hTurret with Becker Automatic Cannon Ammo: 60 of 20mm rounds (4 magazines with 15 rounds in each) Ammo type: HE/AP (High Explosive and Armour Piercing rounds) Rate of fire: 300 rpm Projectile weight: 120/130 g Muzzle velocity: 450/490 m/s Gun weight: 30 kg Mount weight: 10 kg Ammunition total weight: 25 kg Total weight: 65 kg Estimated speed loss: 6 km/hAldis Refractor-type Collimator Sight Additional mass: 2 kgAdditional Gauges Wilhelm Morell Anemometer (45-250 km/h) D.R.G.M liquid Inclinometer (indicates bank while on ground and sideslip while in flight) A.Schlegelmilch engine coolant temperature indicator (0-100 °C) Mechanical Clock Additional mass: 3 kgCockpit illumination lamp for night sorties Additional mass: 1 kgP.u.W. BombsUp to 12 x 12.5 kg P.u.W. General Purpose Bombs Additional mass: 186 kg Ammunition mass: 150 kg Racks mass: 36 kg Estimated speed loss before drop: 4 km/h Estimated speed loss after drop: 2 km/hUp to 3 x 50 kg P.u.W. General Purpose Bombs Additional mass: 186 kg Ammunition mass: 150 kg Racks mass: 36 kg Estimated speed loss before drop: 4 km/h Estimated speed loss after drop: 2 km/hCamera for taking aerial photographs Additional mass: 10 kgRadio transmitter Additional mass: 10 kg Story: Halberstadt CL.II design was a response to an Idflieg (Inspectorate of Aviation Troops) specification issued in august of 1916 for a new "light C-type" with 160-180 engine. The purpose was to create a two-seat escort fighter to protect heavier observation aircraft from attacks of allied fighters. In November of 1916 Idflieg ordered three prototypes of the Halberstadt CL.II with Mercedes D.III engine, with the first ready airplane was rolled out in April of 1917. After a few wing design changes the type was undergoing final tests in Adlesdorf during 2-7 May 1917. Deliveries of machines into frontline service begin by August 1917, being supplied mostly to Schutzstaffeln (Protection flights), and Schlachtstaffeln (Ground attack flights). Its climb and maneuverability was excellent and it was regarded by its crews as very close to such single-engined fighters as the Albatros D.III/V. While the airplane was able to carry photo and radio installations, and primarily used as escort fighter, it was also used as ground attack aircraft. Because of its good maneuverability and ability to rapidly change flight altitude it was able to avoid enemy ground fire, and was successfully used to hit enemy ground troops and other frontline installations. Because of its good performance and ability to hold itself against enemy fighters, and being light and comfortable to fly, the CL.II was preferred by pilots over all other types and remained in service throughout the whole war, serving together with new airplane types. It is not exactly known exactly how many of the CL.II were built, but the production orders of 900 machines correspond to six Idflieg production orders for Halberstadter Flugzeugwerke, plus around of 300 machines by Bayerische Flugzeug Werke AG (in two orders), so it\'s approximately 1200 machines in total. Airplanes of "Flying Circus" Vol.2: Nieuport 28.C1 Engine rotary 9 cyl. Gnome 9N 160 hp Dimensions Height: 2500 mm Length: 6400 mm Wing span: 8160 mm Wing surface: 20 sq.m Weight Empty: 436 kg Takeoff: 698 kg Fuel capacity: 125 l Oil capacity: 25 l Climb rate 1000 m — 2 min. 43 sec. 2000 m — 5 min. 43 sec. 3000 m — 9 min. 30 sec. 4000 m — 14 min. 49 sec. 5000 m — 23 min. 20 sec. Maximum airspeed (IAS) sea level — 203 km/h 1000 m — 190 km/h 2000 m — 177 km/h 3000 m — 165 km/h 4000 m — 150 km/h 5000 m — 136 km/h Service ceiling 5800 m Endurance at 1000m nominal power (combat) — 1 h. 10 min. minimal consumption (cruise) — 1 h. 10 min. Armament Forward firing: 2хVickers Mk.I 7,69mm, 250 rounds per barrel. Additional airplane configurations list: Aldis Refractor-type Collimator Sight (imported from Britain) Additional mass: 2 kgPeltret and Lafage Altimeter (0..5000m) Additional mass: 1 kgTwin Vickers "Balloon" guns Ammo: 400 of 11.43mm rounds Projectile weight: 17,5 g Muzzle velocity: 610 m/s Guns weight: 26 kg Ammo weight: 32 kg Rate of fire: 600 rpm Total additional weight of weapon modification: 58 kgMechanical Clock Additional mass: 1 kgCockpit illumination lamp for night sorties Additional mass: 1 kgL.Maxant Compass Additional mass: 1 kgLe-Chretien Refractor-type Collimator SightAdditional mass: 1 kgSideslip indicator (ball-type) Additional mass: 1 kgE.Badin Anemometer (70..200 km/h at 2000 m and 80..220 km/h at 4000 m) Additional mass: 1 kg Story: The next evolution in the line of fighters made by Nieuport S.A.d E. (Societe Anonyme des Etablissements) Company was the Nieuport 28. Its designers knew that their previous designs were now obsolete and did not allow for better flight characteristics. Therefore, it was decided to use structural features of the SPAD XIII in the design of the new fighter. Some of these features are as follows: larger surface area of the lower wing (a second spar was fitted to it, thus making it a true biplane); a second machine gun was placed left of the centreline behind the engine; and ailerons were fitted to the lower wing instead of the top wing. Its first trial flight occurred on June 5, 1917. Unfortunately, the new fighter could not exceed the flight characteristics of the already-employed SPAD XIII. As a result, French pilots refused to fly it. In all, 208 fighters of this type were built, after which the Nieuport S.A.d E. Company switched to manufacturing the SPAD XIII. The Nieuport 28 entered service with American squadrons in February 1918. Due to an insufficient supply of Vickers machine guns, combat use of the fighter did not begin until the following month. It was primarily used for engaging enemy fighters and balloons but rarely for bomber escort or recon missions behind enemy lines. Pilots noted good climb speed, manoeuvrability, and the sensitivity of its controls. In the course of its combat service, it was found that the plane tended to lose its top wing covering in prolonged dives. There were several incidents of this described by pilots who managed to land despite experiencing such severe damage. Collector's airplanes: Hurricane Mk.II Indicated stall speed in flight configuration: 132...155 km/h Indicated stall speed in landing configuration: 123...144 km/h Dive speed limit: 630 km/h Maximum load factor: 11.0 G Stall angle of attack in flight configuration: 17.6 ° Stall angle of attack in landing configuration: 15.4 ° Maximum true air speed at sea level, 3000 RPM, boost +14: 466 km/h (modification) Maximum true air speed at sea level, 3000 RPM, boost +12: 455 km/h Maximum true air speed at sea level, 3000 RPM, boost +9: 435 km/h Maximum true air speed at 4200 m, 3000 RPM, boost +9: 514 km/h Maximum true air speed at 6550 m, 3000 RPM, boost +9: 543 km/h Service ceiling: 11300 m Climb rate at sea level: 14.0 m/s Climb rate at 3000 m: 13.5 m/s Climb rate at 6000 m: 10.2 m/s Maximum performance turn at sea level: 16.8 s, at 230 km/h IAS. Maximum performance turn at 3000 m: 20.3 s, at 230 km/h IAS. Flight endurance at 3000 m: 3.3 h, at 260 km/h IAS. Takeoff speed: 150...180 km/h Glideslope speed: 150...185 km/h Landing speed: 115..135 km/h Landing angle: 10.0 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates are given for 2850 RPM and boost +9, turn times are given for 3000 RPM and boost +12. Engine: Model: Merlin XX Maximum power in Take-off mode (3000 RPM, boost +12, low gear) at sea level: 1280 HP Maximum power in Climb mode (2850 RPM, boost +9, low gear) at 10000 feet: 1240 HP Maximum power in Climb mode (2850 RPM, boost +9, high gear) at 17500 feet: 1175 HP Maximum power in Combat mode (3000 RPM, boost +12, low gear) at 8500 feet: 1400 HP Maximum power in Combat mode (3000 RPM, boost +14, high gear) at 14750 feet: 1405 HP Engine modes: Max Cruising power (unlimited time): 2650 RPM, boost +7 Climb power (up to 1 hour): 2850 RPM, boost +9 Combat power (up to 5 minutes): 3000 RPM, boost +12/+14 (low gear/hi gear) Combat power (up to 5 minutes): 3000 RPM, boost +14/+16 (low gear/hi gear) (modification) Water rated temperature in engine output: 60..125 °C Water maximum temperature in engine output: 135 °C Oil rated temperature in engine intake: 15..90 °C Oil maximum temperature in engine intake: 105 °C Supercharger gear shift altitude: 13000 feet Empty weight: 2567 kg Minimum weight (no ammo, 10%25 fuel): 2859 kg Standard weight: 3225 kg Maximum takeoff weight: 3894 kg Fuel load: 317 kg / 441.5 l / 97.1 gallons Maximum useful load: 1327 kg Forward-firing armament: 8 x 7.7mm machine gun "Browning .303", 324-338 rounds per gun, 2676 rounds total, 1150 rounds per minute, wing-mounted 8 x 7.7mm machine gun "Browning .303", 370-490 rounds per gun, 3270 rounds total, 1150 rounds per minute, wing-mounted (modification) 12 x 7.7mm machine gun "Browning .303", 324-338 rounds per gun, 3988 rounds total, 1150 rounds per minute, wing-mounted (modification) 12 x 7.7mm machine gun "Browning .303", 328-490 rounds per gun, 4582 rounds total, 1150 rounds per minute, wing-mounted (modification) 4 x 20mm gun "Hispano Mk.II", 90 rounds per gun, 650 rounds per minute, wing-mounted (modification) 2 x 7.7mm machine gun "Browning .303", 650 rounds per gun, 1150 rounds per minute, wing-mounted (modification) 2 x 40mm gun "Vickers Class S", 15 rounds per gun, 125 rounds per minute, wing-mounted (modification) 2 x 12.7mm machine gun "UB", 100 rounds per gun, 1000 rounds per minute, wing-mounted (modification) 2 x 20mm gun "ShVAK", 120 rounds per gun, 800 rounds per minute, wing-mounted (modification) Bombs: 2 x 250 lb general purpose bomb "250 lb. G.P." 2 x 500 lb general purpose bomb "500 lb. G.P." 2 x 104 kg general purpose bomb "FAB-100M" (modification) Rockets: 6 x 7 kg rockets "ROS-82", HE payload mass 2.52 kg (modification) Length: 9.82 m Wingspan: 12.19 m Wing surface: 23.92 m² Combat debut: Autumn 1940 Additional airplane configurations list: Merlin XX engine with +14 lb boost Merlin XX engine with +14 lb boost Estimated speed increase at sea level: 11 km/h Air cleaner for dusty conditions Additional mass: 13 kg Estimated speed loss: 5 km/h Four additional wing-mounted "Browning .303" 7.7mm machine guns with 328 rounds per gun. Additional mass: 100 kg Ammunition mass: 39 kg Guns mass: 55 kg Estimated speed loss: 3 km/h Hispano Mk.II" 20mm wing-mounted guns with 90 rounds per each instead of default "Browning .303" wing-mounted machineguns Additional mass: 195 kg Ammunition mass: 102 kg Guns mass: 228 kg Estimated speed loss: 12 km/h Rear view mirror Additional mass: 1 kg Estimated speed loss: 2 km/h Two BS 12.7 mm wing-mounted machine guns with 100 rounds per each and two ShVAK 20mm wing-mounted guns with 120 rounds per each instead of default "Browning .303" wing-mounted machineguns Additional mass: 59 kg Ammunition mass: 87 kg Guns mass: 124 kg Estimated speed loss: 4 km/h Two wing-mounted "Browning .303" 7.7mm machine guns with 650 rounds per each and two Vickers Class S 40mm gun pods with 15 rounds per each instead of default "Browning .303" wing-mounted machineguns + additional armour plates Additional mass: 390 kg Ammunition mass: 84 kg Guns mass: 323 kg Armour mass: 148 kg Estimated speed loss: 16 km/h Two wing-mounted "Browning .303" 7.7mm machine guns with 650 rounds per each and two Vickers Class S 40mm gun pods with 15 rounds per each instead of default "Browning .303" wing-mounted machineguns Additional mass: 242 kg Ammunition mass: 84 kg Guns mass: 323 kg Estimated speed loss: 14 km/h Operation features: - The engine is equipped with the two-stage mechanical supercharger which should be manually switched at 13000ft altitude. - Engine is equipped with an automatic fuel mixture control which maintains optimal mixture. - Engine RPM has an automatic governor that controls the propeller pitch to maintain the required RPM. - Water and oil temperatures are controlled manually by adjusting the radiator shutter. - Aircraft is equipped with elevator and rudder trimmers. - Landing flaps have hydraulic actuators and can be extended to any angle up to 80°. The speed with the extended flaps is limited to 120 mph. - Airplane tail wheel rotates freely and does not have a lock. - Airplane has differential pneumatic wheel brakes with shared control lever. This means that if the brake lever is held and the rudder pedal the opposite wheel brake is gradually released causing the plane to swing to one side or the other. - Airplane is equipped with a siren that warns a pilot if the throttle is set to low position with landing gear retracted. - It is impossible to open the canopy at high speeds because of the ram air, but there is an emergency jettison handle for bailing out. - Airplane is equipped with upper and bottom formation lights which can be turned on simultaneously or independently. - The gunsight is adjustable: both the target distance and target base can be set. - The gunsight has a sliding sun-filter. - When bombs are installed there is a salvo controller, it has two release modes: single drop or drop two in a salvo. - When rockets are installed there is a salvo controller, it has three launch modes: single fire, fire two in a salvo or fire four in a salvo. La-5 series 8 Indicated stall speed in flight configuration: 165..183 km/h Indicated stall speed in takeoff/landing configuration: 147..162 km/h Dive speed limit: 720 km/h Maximum load factor: 10 G Stall angle of attack in flight configuration: 22.7 ° Stall angle of attack in landing configuration: 15.1 ° Maximum true air speed at sea level, engine mode - Boosted: 544 km/h Maximum true air speed at 3000 m, engine mode - Nominal: 571 km/h Maximum true air speed at 6500 m, engine mode - Nominal: 603 km/h Service ceiling: 9500 m Climb rate at sea level: 18 m/s Climb rate at 3000 m: 13.3 m/s Climb rate at 6000 m: 8.2 m/s Maximum performance turn at sea level: 23.4 s, at 270 km/h IAS. Maximum performance turn at 3000 m: 35.3 s, at 270 km/h IAS. Flight endurance at 3000 m: 1.9 h, at 350 km/h IAS. Takeoff speed: 170..200 km/h Glideslope speed: 200..210 km/h Landing speed: 150..160 km/h Landing angle: 13 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates and turn times are given for Boosted power. Engine: Model: M-82 Maximum power in Boosted mode at sea level: 1700 HP Maximum power in Nominal mode at sea level: 1400 HP Maximum power in Nominal mode at 2100 m: 1550 HP Maximum power in Nominal mode at 5300 m: 1335 HP Engine modes: Nominal (unlimited time): 2400 RPM, 950 mm Hg Boosted power (up to 5 minutes): 2400 RPM, 1140 mm Hg Oil rated temperature in engine output: 55..90 °C Oil maximum temperature in engine output: 125 °C Cylinder head rated temperature: 140..210 °C Cylinder head maximum temperature: 215 °C Supercharger gear shift altitude: 3500 m Empty weight: 2648 kg Minimum weight (no ammo, 10% fuel): 2928 kg Standard weight: 3353 kg Maximum takeoff weight: 3593 kg Fuel load: 370 kg / 521 l Useful load: 945 kg Forward-firing armament: 2 x 20mm gun "SsVAK", 170 rounds, 800 rounds per minute, synchronized Bombs: 2 x 50 kg general purpose bombs "FAB-50sv" 2 x 104 kg general purpose bombs "FAB-100M" Length: 8.672 m Wingspan: 9.8 m Wing surface: 17.51 m^2 Combat debut: September 1942 Additional airplane configurations list: Loadout variants: armour piercing (AP) or high-explosive (HE) rounds only 2 x 50 kg General Purpose Bombs FAB-50sv Additional mass: 120 kg Ammunition mass: 100 kg Racks mass: 20 kg Estimated speed loss before drop: 20 km/h Estimated speed loss after drop: 12 km/h 2 x 104 kg General Purpose Bombs FAB-100M Additional mass: 228 kg Ammunition mass: 208 kg Racks mass: 20 kg Estimated speed loss before drop: 27 km/h Estimated speed loss after drop: 12 km/h Flat frontal section for better visibility Additional mass: 2 kg Estimated speed loss: 2 km/h RPK-10 fixed loop radio compass for navigation with radio beacons Additional mass: 10 kg Estimated speed loss: 0 km/h Late M-82F engine modification with unlimited boosted mode duration. Performance wise, early La-5 aircraft upgraded with this engine are similar to La-5F model. Additional mass: 0 kg Estimated speed loss: 0 km/h Operation features: - Engine has a boost mode. To set boost mode it is necessary to push the boost knob and increase manifold pressure to 1140 mm Hg. - Engine has a two-stage mechanical supercharger which must be manually switched at 3500m altitude. - Engine mixture control is automatic when the mixture lever is set to maximum. It is possible to manually lean the mixture by moving the mixture control to less than maximum. This also reduces fuel consumption during flight. - Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM. - Oil radiator, air cooling intake and outlet shutters is manually controlled. - Air cooling intake shutters should always be open. They should only be closed when there is a possibility of engine overcooling, for example in a dive with idle throttle. - Airplane has trimmers for all flight-controls: pitch, roll, yaw. - Airplane has automatic wing slats. They deploy when the high angle of attack increases which makes pre-stall softer. - Landing flaps have a hydraulic actuator and they can be extended to any angle up to 60°. - Airplane tail wheel rotates freely and does not have a lock. For this reason, it is necessary to confidently and accurately operate the rudder pedals during the takeoff and landing. - Airplane has differential pneumatic wheel brakes with shared control lever. This means that if the brake lever is held and the rudder pedal the opposite wheel brake is gradually released causing the plane to swing to one side or the other. - Airplane has a fuel gauge which shows total remaining fuel. - Cockpit canopy has a weak lock when in the opened position, for this reason the canopy may spontaneously close in a deep dive. Also, it is impossible to open or close canopy at high speed due to strong airflow. The canopy has no emergency release, so bail out requires the speed drop before it. - The control system of wing-mounted bomb racks only allows the dropping of bombs one by one. La-5FN series 2 Indicated stall speed in flight configuration: 168..185 km/h Indicated stall speed in takeoff/landing configuration: 147..159 km/h Dive speed limit: 720 km/h Maximum load factor: 10 G Stall angle of attack in flight configuration: 22.2 ° Stall angle of attack in landing configuration: 15.0 ° Maximum true air speed at sea level, engine mode - Boosted: 552 km/h Maximum true air speed at sea level, engine mode - Nominal: 583 km/h Maximum true air speed at 2500 m, engine mode - Nominal: 605 km/h Maximum true air speed at 6000 m, engine mode - Nominal: 646 km/h Service ceiling: 10500 m Climb rate at sea level: 20 m/s Climb rate at 3000 m: 16.7 m/s Climb rate at 6000 m: 12.5 m/s Maximum performance turn at sea level: 21.0 s, at 320 km/h IAS. Maximum performance turn at 3000 m: 28.0 s, at 340 km/h IAS. Flight endurance at 3000 m: 2.0 h, at 350 km/h IAS. Takeoff speed: 175..195 km/h Glideslope speed: 200..210 km/h Landing speed: 150..160 km/h Landing angle: 13 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates and turn times are given for Boosted power. Engine: Model: M-82FN Maximum power in Boosted mode at sea level: 1850 HP Maximum power in Nominal mode at sea level: 1560 HP Maximum power in Nominal mode at 1550 m: 1630 HP Maximum power in Nominal mode at 4800 m: 1460 HP Engine modes: Nominal (unlimited time): 2400 RPM, 1000 mm Hg Boosted power (up to 10 minutes): 2500 RPM, 1180 mm Hg Oil rated temperature in engine intake: 65..75 °C Oil maximum temperature in engine intake: 85 °C Cylinder head rated temperature: 180..215 °C Cylinder head maximum temperature: 250 °C Supercharger gear shift altitude: 3500 m Empty weight: 2655 kg Minimum weight (no ammo, 10% fuel): 2929 kg Standard weight: 3305 kg Maximum takeoff weight: 3544 kg Fuel load: 334 kg / 464 l Useful load: 896 kg Forward-firing armament: 2 x 20mm gun "SsVAK", 170 rounds, 800 rounds per minute, synchronized Bombs: 2 x 50 kg general purpose bombs "FAB-50sv" 2 x 104 kg general purpose bombs "FAB-100M" Length: 8.672 m Wingspan: 9.8 m Wing surface: 17.51 m^2 Combat debut: June 1943 Additional airplane configurations list: Loadout variants: armour piercing (AP) or high-explosive (HE) rounds only 2 x 50 kg General Purpose Bombs FAB-50sv Additional mass: 120 kg Ammunition mass: 100 kg Racks mass: 20 kg Estimated speed loss before drop: 20 km/h Estimated speed loss after drop: 12 km/h 2 x 104 kg General Purpose Bombs FAB-100M Additional mass: 228 kg Ammunition mass: 208 kg Racks mass: 20 kg Estimated speed loss before drop: 27 km/h Estimated speed loss after drop: 12 km/h Landing light for night flights Additional mass: 2 kg Estimated speed loss: 0 km/h RPK-10 fixed loop radio compass for navigation with radio beacons Additional mass: 10 kg Estimated speed loss: 0 km/h Rear view mirror Additional mass: 1 kg Estimated speed loss: 0 km/h Operation features: - The engine has a boost mode. To engage it, increase the manifold pressure to 1180 mm Hg. Boost only works on 1st supercharger gear. - Engine has a two-stage mechanical supercharger which must be manually switched at 3500m altitude. - Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM. - Oil radiator, air cooling intake and outlet shutters are manually controlled. - Air cooling intake shutters should always be open. They should only be closed when there is a possibility of engine overcooling, for example in a dive with idle throttle. - Aircraft is equipped with elevator and rudder trimmers. - Airplane has automatic wing slats. They deploy when the high angle of attack increases which makes pre-stall softer. - Landing flaps have a hydraulic actuator and they can be extended to any angle up to 60°. - Airplane tail wheel rotates freely and does not have a lock. For this reason, it is necessary to confidently and accurately operate the rudder pedals during the takeoff and landing. - Airplane has differential pneumatic wheel brakes with shared control lever. This means that if the brake lever is held and the rudder pedal the opposite wheel brake is gradually released causing the plane to swing to one side or the other. - Airplane has a fuel gauge which shows total remaining fuel. - Also, it is impossible to open or close canopy at high speed due to strong airflow. The canopy has no emergency release, so bail out requires the speed drop before it. - The control system for the bomb rack only allows to drop bombs one by one. Yak-1(b) series 127 Indicated stall speed in flight configuration: 153..169 km/h Indicated stall speed in takeoff/landing configuration: 132..145 km/h Dive speed limit: 720 km/h Maximum load factor: 10.3 G Stall angle of attack in flight configuration: 18 ° Stall angle of attack in landing configuration: 15.6 ° Maximum true air speed at sea level, engine mode - Nominal, 2550 RPM: 530 km/h Maximum true air speed at 2000 m, engine mode - Nominal, 2700 RPM: 567 km/h Maximum true air speed at 4500 m, engine mode - Nominal, 2700 RPM: 600 km/h Service ceiling: 10600 m Climb rate at sea level: 17.0 m/s Climb rate at 3000 m: 15.0 m/s Climb rate at 6000 m: 9.5 m/s Maximum performance turn at sea level: 19.0 s, at 270 km/h IAS. Maximum performance turn at 3000 m: 24.1 s, at 270 km/h IAS. Flight endurance at 3000 m: 2.0 h, at 350 km/h IAS. Takeoff speed: 160..190 km/h Glideslope speed: 195..205 km/h Landing speed: 135..145 km/h Landing angle: 12 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates and turn times are given for Nominal (2700 RPM) power. Engine: Model: M-105PF Maximum power in Nominal mode (2550 RPM) at sea level: 1240 HP Maximum power in Nominal mode (2700 RPM) at sea level: 1210 HP Maximum power in Nominal mode (2700 RPM) at 800 m: 1260 HP Maximum power in Nominal mode (2700 RPM) at 2700 m: 1200 HP Engine modes: Nominal (unlimited time): 2550/2700 RPM, 1050 mm Hg Water rated temperature in engine output: 70..85 °C Water maximum temperature in engine output: 100 °C Oil rated temperature in engine output: 90..100 °C Oil maximum temperature in engine output: 115 °C Supercharger gear shift altitude: 2300 m Empty weight: 2322 kg Minimum weight (no ammo, 10% fuel): 2543 kg Standard weight: 2887 kg Maximum takeoff weight: 3117 kg Fuel load: 304 kg / 408 l Useful load: 795 kg Forward-firing armament: 20mm gun "SsVAK", 140 rounds, 800 rounds per minute, nose-mounted 12.7mm machine gun "UB", 220 rounds, 1000 rounds per minute, synchronized Bombs: 2 x 50 kg general purpose bombs "FAB-50sv" 2 x 104 kg general purpose bombs "FAB-100M" Length: 8.5 m Wingspan: 10 m Wing surface: 17.15 m^2 Combat debut: April 1943 Additional airplane configurations list: 2 x 50 kg General Purpose Bombs FAB-50sv Additional mass: 120 kg Ammunition mass: 100 kg Racks mass: 20 kg Estimated speed loss before drop: 23 km/h Estimated speed loss after drop: 13 km/h 2 x 104 kg General Purpose Bombs FAB-100M Additional mass: 228 kg Ammunition mass: 208 kg Racks mass: 20 kg Estimated speed loss before drop: 31 km/h Estimated speed loss after drop: 13 km/h Landing light for night flights Additional mass: 2 kg Estimated speed loss: 0 km/h RPK-10 fixed loop radio compass for navigation with radio beacons Additional mass: 10 kg Estimated speed loss: 0 km/h Mirror for view to rear hemisphere Additional mass: 1 kg Estimated speed loss: 0 km/h Operation features: - Engine has a two-stage mechanical supercharger which must be manually switched at 2300m altitude. - Engine mixture control is manual; it is necessary to lean the mixture if altitude is more than 3-4 km for optimal engine operation. Also, leaning the mixture allows a reduction in fuel consumption during flight. - Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM. - Water and oil radiator shutter control is manual. - Airplane has only a flight-control trimmer on the pitch. - Landing flaps have a pneumatic actuator. Flaps can only be fully extended; gradual extending is impossible. Due to the weak force of the actuator the extended landing flaps may be pressed upwards by the airflow if the airspeed is more than 220 km/h. Remember that the flaps will not extend fully in case of high speed. In case of a high-speed landing approach the flaps may extend a few steps further right before landing. - Airplane has a tailwheel control system which is unlocked by the rudder if the rudder pedal is pressed more than 75% of its range. The tailwheel remains locked if pedals are deflected less than 75%. Because of this, it is necessary to avoid large rudder pedal inputs when moving at high speed. - Airplane has differential pneumatic wheel brakes with shared control lever. This means that if the brake lever is held and the rudder pedal the opposite wheel brake is gradually released causing the plane to swing to one side or the other. - Fuel gauges are installed on left and right wing fuel tanks, outside of the cockpit. They show remaining fuel level only when there is less than 80 liters of fuel left in the tank. - It is impossible to open or close the canopy at high speed due to strong airflow. The canopy has no emergency release, so bail out requires the speed drop before it. - The control system for the wing-mounted bomb racks only allows releasing of both bombs together. U-2VS Indicated stall speed in flight configuration: 63..70 km/h Dive speed limit: 240 km/h Maximum load factor: 6.5 G Stall angle of attack in flight configuration: 19° Maximum true air speed at sea level, engine mode - Takeoff, 1750 RPM: 151.7 km/h Maximum true air speed at 500 m, engine mode - Takeoff, 1740 RPM: 150.3 km/h Maximum true air speed at 1000 m, engine mode - Takeoff, 1730 RPM: 148.9 km/h Service ceiling: 3700 m Climb rate: 500 m — 3 min. 5 sec. 1000 m — 6 min. 35 sec. 1500 m — 10 min. 40 sec. 2000 m — 15 min. 24 sec. 2500 m — 21 min. 15 sec. 3000 m — 28 min. 35 sec. 3500 m — 38 min. 20 sec. Maximum performance turn: 22..23 s, at 105..115 km/h IAS. Flight endurance at 500 m: 5 h, at 90 km/h IAS, 1300 RPM. Takeoff speed: 75..85 km/h Glideslope speed: 100 km/h Landing speed: 60..70 km/h Landing angle: 12° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates are given for full-throttle mode and 95 km/h IAS. Note 5: turn rate is given for 1400..1500 RPM with roll 43°..45°. Engine: Model: M-11D Maximum power in Takeoff mode (1750 RPM) at sea level: no less than 125 HP Maximum power in Nominal mode (1700 RPM) at sea level: 118 HP Maximum power in Nominal mode (1700 RPM) at 500 m: 110 HP Maximum power in Nominal mode (1700 RPM) at 1000 m: 105 HP Maximum power in Continuous mode (1640 RPM) at sea level: 107 HP Maximum power in Continuous mode (1640 RPM) at 500 m: 100 HP Maximum power in Continuous mode (1640 RPM) at 1000 m: 95 HP Engine modes: Takeoff/Emergency (5 min) : 1750/1840 RPM Continuous/Nominal (unlimited): 1640/1700 RPM Oil rated temperature in engine output: 70..80 °C Oil maximum temperature in engine output: 115 °C Airscrew: Type 257, D 2.4 m, pitch 1.524 m Empty weight: 748 kg Minimum weight (no ammo, 10% fuel): 927 kg Standard weight: 1007 kg Maximum takeoff weight: 1350 kg Fuel load: 90 kg / 126 l Useful load: 350 kg Forward-firing armament: 1 x 7.62mm machine gun "ShKAS", 500 rounds, 1800 rounds per minute, wing-mounted (modification) Defensive armament: Rear-facing: 7.62mm machine gun "ShKAS", 400 rounds, 1800 rounds per minute (modification) Bombs: 2 x 50 kg general purpose bombs "FAB-50sv" 4 x 50 kg general purpose bombs "FAB-50sv" 6 x 50 kg general purpose bombs "FAB-50sv" 2 x 104 kg general purpose bombs "FAB-100M" 2 x 50 kg general purpose bombs "FAB-50sv" and 2 x 104 kg general purpose bombs "FAB-100M" Height: 2.9 m Length: 8.17 m Wingspan of upper wing: 11.4 m Wingspan of lower wing: 10.65 m Wing surface: 33.15 m² The U-2 aircraft was developed under N.N. Polikarpov supervision in 1923-1928. It was designed as a simple, sturdy, and easy to handle two-seater aircraft for flight schools. It went airborne for the first time on June 24, 1927, but many improvements to its design were made afterwards to improve its climb rate. The upgraded plane went into production in 1929 after the first flight on January 7, 1928. Flight instructors and pilot candidates liked the plane - it forgave the typical mistakes of the trainees, was hard to stall and easy to recover, predictable at high angles of attack and had a low landing speed. Many future aces learned to fly in this \'flying school-desk\'. It was the first aircraft for the majority of VVS pilots. Several modifications of this aircraft were developed: ambulance S-1 and S-2, passenger U-2SP and U-2L, agriculture U-2AP and military U-2VS. The military modification could carry up to 300 kg of bombs and was equipped with a defensive MG turret. During WWII, it was mainly used as a low-altitude bomber and recon plane. It was a very hard target for enemy fighters at low altitudes because of its low speed, resulting in its relatively high survivability rate. It was used by the famous "night witches", female pilots and navigators of 46th Guards night bomber regiment. The model was renamed to Po-2 to honor N.N. Polikarpov after his passing in 1944. Additional airplane configurations list: Rear turret with ShKAS 7.62mm machinegun with 400 rounds Additional mass: 34 kg Estimated speed loss: 2 km/hWing-mounted 7.62mm ShKAS machinegun with 500 rounds Additional mass: 27 kg Estimated speed loss: 3 km/hUnderwing and underbelly racks with bombs2 x FAB-50sv bombs 2 x 50 kg General Purpose Bombs FAB-50sv Additional mass: 104 kg Ammunition mass: 100 kg Racks mass: 4 kg Estimated speed loss before drop: 5 km/h Estimated speed loss after drop: 1 km/h4 x FAB-50sv bombs 4 x 50 kg General Purpose Bombs FAB-50sv Additional mass: 208 kg Ammunition mass: 200 kg Racks mass: 8 kg Estimated speed loss before drop: 10 km/h Estimated speed loss after drop: 2 km/h6 x FAB-50sv bombs 6 x 50 kg General Purpose Bombs FAB-50sv Additional mass: 312 kg Ammunition mass: 300 kg Racks mass: 12 kg Estimated speed loss before drop: 16 km/h Estimated speed loss after drop: 3 km/h2 x FAB-100M bombs 2 x 104 kg General Purpose Bombs FAB-100M Additional mass: 212 kg Ammunition mass: 208 kg Racks mass: 4 kg Estimated speed loss before drop: 7 km/h Estimated speed loss after drop: 1 km/h2 x FAB-100M bombs and 2 x FAB-50sv bombs 2 x 104 kg General Purpose Bombs FAB-100M and 2 x 50 kg General Purpose Bombs FAB-50sv Additional mass: 316 kg Ammunition mass: 308 kg Racks mass: 8 kg Estimated speed loss before drop: 13 km/h Estimated speed loss after drop: 2 km/hNavigation lights Additional mass: 4 kgLanding light for night flights Additional mass: 2 kg Estimated speed loss: 1 km/hHorizon indicator AGP-2 Additional mass: 2 kg Estimated speed loss: 0 km/hRadio transmitter RSI-4 Additional mass: 12.6 kg Estimated speed loss: 0 km/hExplosive and armour-piercing unguided rockets82 mm ROS-82 x 4: Additional mass: 40 kg Ammunition mass: 28 kg Racks mass: 12 kg Estimated speed loss before launch: 2 km/h Estimated speed loss after launch: 1 km/h82 mm ROS-82 x 8: Additional mass: 80 kg Ammunition mass: 56 kg Racks mass: 24 kg Estimated speed loss before launch: 4 km/h Estimated speed loss after launch: 2 km/h82 mm RBS-82 x 4: Additional mass: 72 kg Ammunition mass: 60 kg Racks mass: 12 kg Estimated speed loss before launch: 3 km/h Estimated speed loss after launch: 1 km/h82 mm RBS-82 x 8: Additional mass: 144 kg Ammunition mass: 120 kg Racks mass: 24 kg Estimated speed loss before launch: 4 km/h Estimated speed loss after launch: 2 km/h132 mm ROS-132 x 8: Additional mass: 224 kg Ammunition mass: 184 kg Racks mass: 40 kg Estimated speed loss before launch: 8 km/h Estimated speed loss after launch: 4 km/h Operational features: - There is no engine supercharger. - The fuel mixture control is manual: the mixture should be leaned as the altitude increases for optimal engine functioning and to reduce the fuel consumption while flying level. - The fixed pitch propeller requires controlling the engine RPM manually. - The tail skid is linked to the rudder (8° maximum tilt). - There are no wheel brakes. - There is no electric generator in the default aircraft configuration, so electric lights and Pitot tube warmer (which consumes up to 226W) are fed from 24V battery (10 Ah capacity at 1 A current in standard conditions). To power the RSI-4 radio station, GS-10-350 electric generator is installed along with it. - Please note that with all possible modifications and full fuel the total aircraft weight is 1390 kg, more than its maximum takeoff weight. P-38J-25 Indicated stall speed in flight configuration: 179..220 km/h (111..137 mph) Indicated stall speed in takeoff/landing configuration: 149..185 km/h (93..115 mph) Dive speed limit: 725 km/h (450 mph) Maximum load factor: 9.0 G Stall angle of attack in flight configuration: 14.1 ° Stall angle of attack in landing configuration: 11.5 ° Maximum true air speed at sea level, engine mode - WEP: 557 km/h (346 mph) Maximum true air speed at 7860 m (25800 feet), engine mode - WEP: 674 km/h (419 mph) Maximum true air speed at sea level, engine mode - Combat: 540 km/h (336 mph) Maximum true air speed at 8500 m (27890 feet), engine mode - Combat: 670 km/h (416 mph) Service ceiling: 12350 m (40500 feet) Climb at engine mode - WEP Climb rate at sea level: 20.4 m/s (4020 feet/min) Climb rate at 3000 m (9843 feet): 19.1 m/s (3758 feet/min) Climb rate at 6000 m (19685 feet): 15.0 m/s (2953 feet/min) Climb at engine mode - Combat Climb rate at sea level: 12.8 m/s (2518 feet/min) Climb rate at 3000 m (9843 feet): 11.5 m/s (2258 feet/min) Climb rate at 6000 m (19685 feet): 9.4 m/s (1844 feet/min) Maximum performance turn at sea level: 20.0 s, at 310 km/h (195 mph) IAS. Maximum performance turn at 3000 m (9843 feet): 28.3 s, at 320 km/h (200 mph) IAS. Flight endurance at 3000 m (9843 feet): 5.8 h, at 350 km/h (217 mph) IAS. Takeoff speed: 160..175 km/h (100..110 mph) Glideslope speed: 185..210 km/h (115..130 mph) Landing speed: 150..175 km/h (95..110 mph) Landing angle: 7.0 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass and 70% of fuel. Note 4: turn times are given for WEP power. Engine: Model: Allison V-1710-89 (left) and V-1710-91 (right) Maximum power in WEP mode at sea level: 1550 HP Maximum power in WEP mode at 7860 m (25800 feet): 1505 HP Engine modes: Cruise (unlimited time): 2600 RPM, 44 inch Hg Combat power (up to 15 minutes): 3000 RPM, 54 inch Hg WEP (up to 5 minutes): 3000 RPM, 60 inch Hg Maximum continuous turbocharger RPM: 24000 Maximum turbocharger RPM for up to 15 minutes: 26400 Water rated temperature in engine output: 85 °C Water maximum temperature in engine output: 105 °C Oil rated temperature in engine output: 105 °C Oil maximum temperature in engine output: 115 °C Supercharger gear shift altitude: single gear Empty weight: 6356 kg (14013 lb) Minimum weight (no ammo, 10% fuel): 6662 kg (14687 lb) Standard weight: 7890 kg (17395 lb) Maximum takeoff weight: 10113 kg (22295 lb) Fuel load: 1132 kg (2496 lb) / 1575 l (416 gal) Useful load: 3757 kg (8282 lb) Forward-firing armament: 20mm gun "M2", 150 rounds, 650 rounds per minute, nose-mounted 4 x 12.7mm machine gun "M2.50", 300 rounds, 850 rounds per minute, nose-mounted It is possible to increase the ammo load to 500 rounds per gun. Bombs: Up to six 500 lb general purpose bomb "M64" Up to four 1000 lb general purpose bomb "M65" Up to two 2000 lb general purpose bomb "M66" Rockets: 6 x unguided rockets "M8" in two "M10" launchers that can be jettisoned Length: 10.89 m (35.73 feet) Wingspan: 15.85 m (52 feet) Wing surface: 30.4 m² (327 feet²) Combat debut: 1944 Additional airplane configurations list: Additional ammo for machine guns: 500 for each gun. Additional mass: 99.3 kg (218.9 lbs) Estimated speed loss: 0 km/hGeneral purpose bombs2 x 500 lb General Purpose Bomb M64: Additional mass: 508 kg (1120 lbs) Estimated speed loss before drop: 9 km/h (5.5 mph) Estimated speed loss after drop: 2 km/h (1.2 mph)2 x 1000 lb General Purpose Bomb M65: Additional mass: 1024 kg (2324 lbs) Estimated speed loss before drop: 19 km/h (11.6 mph) Estimated speed loss after drop: 2 km/h (1.2 mph)2 x 2000 lb General Purpose Bomb M66: Additional mass: 1858 kg (4096 lbs) Estimated speed loss before drop: 23 km/h (14.2 mph) Estimated speed loss after drop: 2 km/h (1.2 mph)Additional bomb racks6 x 500 lb General Purpose Bomb M64: Additional mass: 1568 kg (3457 lbs) Ammunition mass: 1524 kg (3360 lbs) Rack mass: 44 kg (97 lbs) Estimated speed loss before drop: 52 km/h (32.3 mph) Estimated speed loss after drop: 19 km/h (12.0 mph) 4 x 1000 lb General Purpose Bomb M65: Additional mass: 2092 kg (4612 lbs) Ammunition mass: 2048 kg (4515 lbs) Rack mass: 44 kg (97 lbs) Estimated speed loss before drop: 60 km/h (37.0 mph) Estimated speed loss after drop: 19 km/h (12.0 mph)6 x M8 rockets in jettisonable M10 launchers Additional mass: 171.9 kg (379 lbs) Ammunition mass: 115.9 kg (256 lbs) Racks mass: 56 kg (123 lbs) Estimated speed loss before launch: 18 km/h (11.4 mph) Estimated speed loss after launch: 13 km/h (8.2 mph) Estimated speed loss after drop: 4 km/h (2.5 mph)Fixed loop Bendix MN-26 radio compass for navigation with radio beacons Additional mass: 17,5 kg (38.6 lbs) Estimated speed loss: 1 km/h Operation features: - In addition to the automatic single-stage supercharger, each engine is equipped with the automatic turbo-supercharger. - The turbo-supercharger is powered by the engine exhaust backpressure and is regulated automatically by the pilot throttle control in the cockpit using the shutters on the exhaust pipes. - It should be noted that turbocharger RPM changes relatively slowly and not immediately after a control lever adjustment. For instance, during takeoff it's necessary to keep the brakes pressed for several seconds after moving the throttle to takeoff position and begin the run only when the turbocharger RPM increases sufficiently to reach 54 inches of pressure. - The automatic fuel mixture control maintains optimal mixture if mixture lever is set to Auto Rich (70%) position. To use automatic mixture leaning to reduce the fuel consumption during flight set the mixture lever to Auto Lean (30%) position. In a case of malfunction of the automatic mixture control, the mixture lever should be set to Full Rich (move the lever completely forward) position. To stop the engine, set it to the Idle Cut Off (0%) position. - The automatic engine governor keeps the set engine RPM by adjusting the propeller pitch using an electric actuator (it is possible to turn it off and control the propeller pitch manually). The propellers can be feathered. - The aircraft has pitch and yaw flight-control trimmers. - Landing flaps have a hydraulic actuator and can be extended to any angle up to 40°. There is also a fixed "maneuver" flaps position that can be set by a short flaps button press ("F" by default). - The aircraft is equipped with hydraulic aileron actuators, making their operation and good roll performance at high speeds possible. The actuators are turned on using a special valve on the left side of the cockpit and require at least 1200 psi pressure in the hydraulic system, so they should be turned off if there is only one engine running. In the sim, they are turned on and off automatically. - The aircraft has independent left and right hydraulic wheel brake controls. To apply either brake push the upper part of the rudder pedal. - The aircraft is equipped with a parking brake system. - The landing gear indicator lamp lights up if the landing gear is neither extended nor retracted. The extension of the nose wheel can also be checked by its reflection in the mirrors on the inner sides of the engine nacelles and by the pressure drop in the hydraulic system during the landing gear operation. - There are signal lamps warning about the low fuel level in the outer wing tanks (the primary fuel source) and separate fuel indicators for the left and right fuel tank pairs. - The canopy has an emergency release system for bailouts. - The windows on the sides of the canopy can be lowered during flight, but this can cause the excessive shaking of the plane. - The electric bomb controller allows dropping the bombs one by one from the left and right racks or by pairs. - The unguided rockets are launched using the electric controller which allows single, pair, triple and salvo (all rockets at 0.1 seconds interval) launch. The rocket containers are jettisonable. P-40E-1 Indicated stall speed in flight configuration: 153..176 km/h Indicated stall speed in takeoff/landing configuration: 141..164 km/h Dive speed limit: 860 km/h Maximum load factor: 12.2 G Stall angle of attack in flight configuration: 14 ° Stall angle of attack in landing configuration: 12.6 ° Maximum true air speed at sea level, engine mode - Take-off: 494 km/h Maximum true air speed at 5000 m, engine mode - Take-off: 601 km/h Service ceiling: 9200 m Climb rate at sea level: 12.5 m/s Climb rate at 3000 m: 10 m/s Climb rate at 6000 m: 3.7 m/s Maximum performance turn at sea level: 24.3 s, at 270 km/h IAS. Maximum performance turn at 3000 m: 36.1 s, at 270 km/h IAS. Flight endurance at 3000 m: 2.8 h, at 350 km/h IAS. Takeoff speed: 160..190 km/h Glideslope speed: 210..220 km/h Landing speed: 140..145 km/h Landing angle: 13.9 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates are given for Take-off power, turn times are given for Maximum possible power. Engine: Model: V-1710-39 Maximum power in Maximum Possible power mode at sea level: 1470 HP Maximum power in Take-off mode at sea level: 1150 HP Maximum power in Nominal mode at sea level: 900 HP Maximum power in Combat mode at 12000 feet: 1150 HP Maximum power in Nominal mode at 10800 feet: 1000 HP Engine modes: Nominal (unlimited time): 2600 RPM, 37.2 inch Hg Combat power (up to 5 minutes): 3000 RPM, 42 inch Hg Take-off power (up to 2 minutes): 3000 RPM, 45.5 inch Hg Maximum Possible power (prohibited by flight manual): 3000 RPM, 56.0 inch Hg Water rated temperature in engine output: 105..115 °C Water maximum temperature in engine output: 125 °C Oil rated temperature in engine intake: 70..85 °C Oil maximum temperature in engine intake: 90 °C Supercharger gear shift altitude: single gear Empty weight: 3073 kg Minimum weight (no ammo, 10% fuel): 3264.2 kg Standart weight: 3819.1 kg Maximum takeoff weight: 4414 kg Fuel load: 404 kg / 561 l Useful load: 1341 kg Forward-firing armament: 6 x 12.7mm machine gun "M2.50", 235 rounds, 850 rounds per minute, wing-mounted Bombs: 254 kg general purpose bomb "FAB-250sv" 512 kg general purpose bomb "FAB-500M" Rockets: 4 x 7 kg rockets "ROS-82", HE payload mass 2.52 kg Length: 9.05 m Wingspan: 11.4 m Wing surface: 21.92 m^2 Combat debut: December 1941 Additional airplane configurations list: Removal of 2 external wing-mounted machine guns to reduce total weight Weight savings: 156 kg Removed ammunition mass: 64 kg Removed guns mass: 92 kg Estimated additional speed: 3 km/h Additional ammo for machine guns: 312 for internal ones, 291 for middle ones, 240 for external ones (instead of 235 per each) or 615 per each for 4x MG. 6 machineguns: Additional mass: 38 kg Estimated speed loss: 0 km/h 4 machineguns: Additional mass: 207 kg Estimated speed loss: 2 km/h 254 kg General Purpose Bomb FAB-250sv Additional mass: 264 kg Ammunition mass: 254 kg Rack mass: 10 kg Estimated speed loss before drop: 19 km/h Estimated speed loss after drop: 7 km/h 254 kg General Purpose Bomb FAB-500M Additional mass: 522 kg Ammunition mass: 512 kg Rack mass: 10 kg Estimated speed loss before drop: 36 km/h Estimated speed loss after drop: 7 km/h 4 x 82mm High Explosive unguided rockets ROS-82 Additional mass: 40 kg Ammunition mass: 28 kg Racks mass: 12 kg Estimated speed loss before launch: 13 km/h Estimated speed loss after launch: 10 km/h Mirror for view to rear hemisphere Additional mass: 1 kg Estimated speed loss: 2 km/h Operation features: - Engine has no manifold pressure automatic governor. For this reason, manifold pressure not only depends on throttle position, but also from RPM and altitude. This requires additional checking of manifold pressure to not cause engine damage. - Engine has a single-stage mechanical supercharger which does not require manual control. - Engine is equipped with an automatic fuel mixture control which maintains optimal mixture if mixture lever is set to Auto Rich (66%) position. To use automatic mixture leaning to reduce fuel consumption during flight it is necessary to set mixture lever to Auto Lean (33%) position. In the case of mulfunction of the automatic mixture control the mixture lever should be set to Full Rich (100%) position. To stop the engine mixture lever should be set to the Cut Off (0%) position. - Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM. Also it is possible to turn off the governor and control propeller pitch manually. - Water and oil radiators shutters are joint with engine cowl outlet shutters and manually operated. - Airplane has a very small stability margin in yaw. When angle of side slip is more than 12° plane becomes unstable in yaw and starts to increase the side slip angle by itself. Because of this, it is necessary to accurately operate the rudder pedals and pay attention to the side slip indicator. - Airplane has trimmers for all flight-controls: pitch, roll, yaw. - Landing flaps have a hydraulic actuator and they can be extended to any angle up to 45°. - Airplane has a tailwheel control system which is unlocked by the rudder if the rudder pedal is pressed more than half of its range. The tailwheel remains locked if pedals are deflected less than half way. Because of this, it is necessary to avoid large rudder pedal inputs when moving at high speed. - Airplane has independent left and right hydraulic wheel brakes. To brake it is necessary to push upper part of the rudder pedal. - Airplane is equipped with a parking brake system. - Airplane has three fuel gauges which shows the level in each fuel tank. - It is impossible to open or close canopy at high speed due to strong airflow. The canopy has an emergency release system for bail out. - Airplane is equipped with mechanical releasing system for a single bomb. - When rockets are installed a salvo controller can be used, it has three launch modes: single fire, fire two in a salvo or fire four in a salvo. - The gunsight has a sliding sun-filter. There is also a back-up mechanical sight which can be used if main sight is damaged. Supermarine Spitfire Mk.VB Indicated stall speed in flight configuration: 137..144 km/h Indicated stall speed in takeoff/landing configuration: 129..135 km/h Dive speed limit: 725 km/h Maximum load factor: 12.5 G Stall angle of attack in flight configuration: 18.8 ° Stall angle of attack in landing configuration: 16.0 ° Merlin 46 engine: Maximum true air speed at sea level, 3000 RPM, boost +9: 457 km/h Maximum true air speed at sea level, 3000 RPM, boost +16: 515 km/h Maximum true air speed at 7400 m, 3000 RPM, boost +9: 597 km/h Maximum true air speed at 5000 m, 3000 RPM, boost +16: 604 km/h Service ceiling: 12000 m Climb rate at sea level: 12.9 m/s Climb rate at 3000 m: 13.1 m/s Climb rate at 6000 m: 12.0 m/s Maximum performance turn at sea level: 25 s, at 270 km/h IAS. Maximum performance turn at 3000 m: 30 s, at 260 km/h IAS. Merlin 45 engine: Maximum true air speed at sea level, 3000 RPM, boost +9: 480 km/h Maximum true air speed at sea level, 3000 RPM, boost +16: 535 km/h Maximum true air speed at 6000 m, 3000 RPM, boost +9: 590 km/h Maximum true air speed at 3500 m, 3000 RPM, boost +16: 596 km/h Service ceiling: 11200 m Climb rate at sea level: 14.5 m/s Climb rate at 3000 m: 14.7 m/s Climb rate at 6000 m: 11.4 m/s Maximum performance turn at sea level: 22 s, at 270 km/h IAS. Maximum performance turn at 3000 m: 28.2 s, at 260 km/h IAS. Flight endurance at 3000 m: 1 h 45 m, at 350 km/h IAS. Takeoff speed: 160..170 km/h Glideslope speed: 145..160 km/h Landing speed: 130..135 km/h Landing angle: 12.5 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates are given for 2850 RPM and boost +9, turn times are given for 3000 RPM and boost +9. Engine: Model: Merlin 46 Maximum power in Take-off mode (3000 RPM, boost +12) at sea level: 1100 HP Maximum power in Emergency Max All Out mode (3000 RPM, boost +16) at 14000 feet: 1400 HP Maximum power in International power mode (2850 RPM, boost +9) at 19000 feet: 1115 HP Model: Merlin 45 Maximum power in Take-off mode (3000 RPM, boost +12) at sea level: 1185 HP Maximum power in Emergency Max All Out mode (3000 RPM, boost +16) at 9000 feet: 1455 HP Maximum power in International power mode (2850 RPM, boost +9) at 14200 feet: 1170 HP Engine modes: Max Cruising power (unlimited time): 2650 RPM, boost +7 International power (up to 30 minutes): 2850 RPM, boost +9 Emergency Max All Out power (up to 5 minutes): 3000 RPM, boost +16 Water rated temperature in engine output: 105..115 °C Water maximum temperature in engine output: 125 °C Oil rated temperature in engine intake: 70..85 °C Oil maximum temperature in engine intake: 105 °C Supercharger gear shift altitude: single gear Empty weight: 2415 kg Minimum weight (no ammo, 10%25 fuel): 2732 kg Standard weight: 2979 kg Fuel load: 274 kg / 386 l / 85 gallons Useful load: 564 kg Forward-firing armament: 2 x 20mm guns "Hispano Mk.II", 60 rounds per gun, 650 rounds per minute, wing-mounted 4 x 7.92mm machine gun "Browning .303", 350 rounds per gun, 1150 rounds per minute, wing-mounted Length: 9.2 m Wingspan: 11.21 m Wing surface: 22.48 m^2 Combat debut: Winter 1941 (In Battle of Kuban - at Spring 1943) Additional airplane configurations list: Merlin 45 engine Additional mass: 0 kg Estimated speed loss: 0 km/h Mirror for view to rear hemisphere Additional mass: 1 kg Estimated speed loss: 2 km/h Operation features: - Engine is equipped with the automatic governor of the manifold pressure that works when the throttle is set to 1/3 position or above. It is neccessary to turn the automatic governor off to set the boost value to +16. - Engine has a single stage mechanical supercharger which does not require manual control. - Engine is equipped with an automatic fuel mixture control which maintains optimal mixture if mixture lever is set to the forward position. To use automatic mixture leaning to reduce fuel consumption during flight move the mixture lever to backward position. - Engine RPM has an automatic governor that controls the propeller pitch to maintain the required RPM. - The water radiator is operated manually, while the oil radiator is unadjustable. - Aircraft has a neutral static stability. The elevator effectiveness is high, so the aircraft should be controlled carefully, not giving too much flight stick input. - Aircraft becomes unstable with extended landing flaps. - Aircraft is equipped with elevator and rudder trimmers. - Landing flaps have a pneumatic actuator so they can be extended to maximum position only. Speed with extended landing flaps is limited to 150 mph. - Airplane tail wheel rotates freely and does not have a lock. Since the landing gear wheels are relatively close to each other, it is necessary to confidently and accurately operate the rudder pedals during the takeoff and landing. - Airplane has differential pneumatic wheel brakes with shared control lever. This means that if the brake lever is held and the rudder pedal the opposite wheel brake is gradually released causing the plane to swing to one side or the other. - Airplane is equipped with a siren that warns a pilot if the throttle is set to low position with landing gear retracted. - It is impossible to open or close the canopy at high speed due to strong airflow. The canopy has an emergency release system for bailouts. - Airplane is equipped with upper and bottom formation lights which can be turned on simultaneously or independently. - The gunsight is adjustable: both the target distance and target base can be set. - The gunsight has a sliding sun-filter. Bf 109 G-6 Indicated stall speed in flight configuration: 160..177 km/h Indicated stall speed in takeoff/landing configuration: 153..169 km/h Dive speed limit: 850 km/h Maximum load factor: 10.5 G Stall angle of attack in flight configuration: 19.8 ° Stall angle of attack in landing configuration: 17 ° Maximum true air speed at sea level, engine mode - Emergency: 529 km/h Maximum true air speed at sea level, engine mode - Combat: 505 km/h Maximum true air speed at 2000 m, engine mode - Combat: 547 km/h Maximum true air speed at 7000 m, engine mode - Combat: 632 km/h Service ceiling: 11800 m Climb rate at sea level: 20.1 m/s Climb rate at 3000 m: 18.8 m/s Climb rate at 6000 m: 15.2 m/s Maximum performance turn at sea level: 21.5 s, at 270 km/h IAS. Maximum performance turn at 3000 m: 28.0 s, at 270 km/h IAS. Flight endurance at 3000 m: 2.2 h, at 350 km/h IAS. Takeoff speed: 155..180 km/h Glideslope speed: 195..205 km/h Landing speed: 150..155 km/h Landing angle: 13.7 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates and turn times are given for Combat power. Engine: Model: DB-605A Maximum power in Emergency mode at sea level: 1480 HP Maximum power in Emergency mode at 5600 m: 1360 HP Maximum power in Combat mode at sea level: 1310 HP Maximum power in Combat mode at 5800 m: 1250 HP Engine modes: Nominal (unlimited time): 2300 RPM, 1.15 ata Combat power (up to 30 minutes): 2600 RPM, 1.3 ata Emergency power (up to 1 minute): 2800 RPM, 1.42 ata Water rated temperature in engine output: 100..102 °C Water maximum temperature in engine output: 115 °C Oil rated temperature in engine intake: 70..80 °C Oil maximum temperature in engine intake: 85 °C Supercharger gear shift altitude: fluid coupling Empty weight: 2583 kg Minimum weight (no ammo, 10% fuel): 2734 kg Standard weight: 3100 kg Maximum takeoff weight: 3400 kg Fuel load: 304 kg / 400 l Useful load: 817 kg Forward-firing armament: 20mm gun "MG 151/20", 200 rounds, 700 rounds per minute, nose-mounted 2 x 13mm machine gun "MG 131", 300 rounds, 900 rounds per minute, synchronized 2 x 20mm gun "MG 151/20", 135 rounds, 700 rounds per minute, wing-mounted (modification) 30mm gun "MK 108", 65 rounds, 650 rounds per minute, nose-mounted (modification) Bombs: Up to 4 x 55 kg general purpose bombs "SC 50" 249 kg general purpose bomb "SC 250" Length: 8.94 m Wingspan: 9.97 m Wing surface: 16.1 m^2 Combat debut: february 1943 Additional airplane configurations list: MG 151/20 20mm guns in wing-mounted gun pods with 135 rounds per each Additional mass: 212 kg Ammunition mass: 55 kg Guns mass: 157 kg Estimated speed loss: 12 km/h MK 108 30mm nose-gun with 65 rounds Removed mass: 6 kg Ammunition mass: 28 kg Gun mass: 58 kg Estimated speed loss: 0 km/h 4 x 55 kg General Purpose Bombs SC 50 Additional mass: 260 kg Ammunition mass: 220 kg Racks mass: 40 kg Estimated speed loss before drop: 51 km/h Estimated speed loss after drop: 11 km/h 249 kg General Purpose Bomb SC 250 Additional mass: 279 kg Ammunition mass: 249 kg Racks mass: 30 kg Estimated speed loss before drop: 31 km/h Estimated speed loss after drop: 10 km/h Alternative pilot protection: armoured transparent triplex head rest for better visibility Additional mass: 10 kg Estimated speed loss: 0 km/h Removed pilot armoured headrest for improved field of view Weight savings: 8 kg Estimated speed loss: 0 km/h Fixed loop radio compass for navigation with radio beacons Peilrahmen PR 16 Additional mass: 10 kg Estimated speed loss: 0 km/h Operation features: - Airplane has a wide automatization of the engine systems, in fact, to control speed it is only necessary to use the throttle lever. There is no need to manually set engine revolutions and mixture or supercharger gear in normal flight. - In addition to full-automatic mode there is a special manual control mode for the radiator shutters, which can be used in specific situations. - To reduce swinging during taxiing due to prop-wash the propeller pitch control should be switched to manual mode and pitch should be reduced to minimum. - Airplane has no flight-control trimmers. Airplane is equipped with bendable trim tabs that can be set pre-flight by ground personnel. - Airplane has a manually controlled horizontal stabilizer. It should be set to +1° before takeoff and to -4°...-5° before landing. Also, it may be used to trim the flight stick during the flight. In a deep dive the stabilizer should be set so that the pilot must push the flight stick forward to maintain the dive angle. - Airplane has automatic wing slats. They deploy when the high angle of attack increases which makes pre-stall softer. - Airplane has a manual mechanical system for retracting the landing flaps, for this reason it is necessary to extend landing flaps well before final approach. Markers on the left-wing flap indicate how far the flaps are extended. The flaps can be extended to any angle up to 40°. - Airplane has a manual tail wheel lock. Wheel should be locked when taxiing straight for a long distance and before takeoff and landing. - Airplane has independent left and right hydraulic wheel brake controls. To apply either brake push the upper part of the rudder pedal. - Airplane has a fuel gauge which shows total fuel remaining. Also, it has an emergency fuel warning light (80 liters). - The design of the cockpit canopy does not allow it to be opened during flight. The canopy should be closed before takeoff to prevent damage. The canopy has an emergency release system for bailouts. - The control system for the bomb rack only allows to drop bombs one by one. - The gunsight has a sliding sun-filter. Fw 190 A-3 Indicated stall speed in flight configuration: 166..189 km/h Indicated stall speed in takeoff/landing configuration: 166..172 km/h Dive speed limit: 850 km/h Maximum load factor: 11 G Stall angle of attack in flight configuration: 19.5° Stall angle of attack in landing configuration: 18.1° Maximum true air speed at sea level, engine mode - Emergency: 560 km/h Maximum true air speed at 3000 m, engine mode - Emergency: 581 km/h Maximum true air speed at 6400 m, engine mode - Emergency: 662 km/h Maximum true air speed at sea level, engine mode - Combat: 535 km/h Maximum true air speed at 3000 m, engine mode - Combat: 562 km/h Maximum true air speed at 6000 m, engine mode - Combat: 626 km/h Service ceiling: 10800 m Climb rate at sea level: 16.0 m/s Climb rate at 3000 m: 12.7 m/s Climb rate at 6000 m: 10.3 m/s Maximum performance turn at sea level: 23.0 s, at 280 km/h IAS. Maximum performance turn at 3000 m: 28.0 s, at 280 km/h IAS. Flight endurance at 3000 m: 3.2 h, at 350 km/h IAS. Takeoff speed: 170..210 km/h Glideslope speed: 205..215 km/h Landing speed: 160..170 km/h Landing angle: 12.5° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates are given for Combat power, turn times are given for Emergency power. Engine: Model: BMW-801D Maximum power in Emergency mode at sea level: 1700 HP Maximum power in Emergency mode at 5700 m: 1440 HP Maximum power in Combat mode at 700 m: 1520 HP Maximum power in Combat mode at 5300 m: 1320 HP Engine modes: Nominal (unlimited time): 2300 RPM, 1.2 ata Combat power (up to 30 minutes): 2400 RPM, 1.32 ata Emergency power (up to 3 minutes): 2700 RPM, 1.42 ata Oil rated temperature in engine intake: 60..70 °C Oil maximum temperature in engine intake: 85 °C Oil rated temperature in engine output: 105 °C Oil maximum temperature in engine output: 120 °C Cylinder head rated temperature: 180 °C Cylinder head maximum temperature: 220 °C Supercharger gear shift altitude: automatic Empty weight: 3148 kg Minimum weight (no ammo, 10% fuel): 3330 kg Standard weight: 3855 kg Maximum takeoff weight: 4385 kg Fuel load: 409 kg / 524 l Useful load: 1237 kg Forward-firing armament: 2 x 20mm gun "MG 151/20", 250 rounds, 700 rounds per minute, synchronized 2 x 7.92mm machine gun "MG 17", 900 rounds, 1200 rounds per minute, synchronized 2 x 20mm gun "MG FF", 90 rounds, 540 rounds per minute, wing-mounted (modification) Bombs: Up to 4 x 55 kg general purpose bombs "SC 50" 249 kg general purpose bomb "SC 250" 500 kg general purpose bomb "SC 500" Length: 8.85 m Wingspan: 10.51 m Wing surface: 18.3 m^2 Combat debut: March 1942 Additional airplane configurations list: MG FF/M 20mm additional wing-mounted guns with 60 rounds per each Additional mass: 123 kg Ammunition mass: 29 kg Guns mass: 94 kg Estimated speed loss: 7 km/h MG FF/M 20mm additional wing-mounted guns with 90 rounds per each Additional mass: 144 kg Ammunition mass: 50 kg Guns mass: 94 kg Estimated speed loss: 8 km/h 4 x 55 kg General Purpose Bombs SC 50 Additional mass: 280 kg Ammunition mass: 220 kg Racks mass: 60 kg Estimated speed loss before drop: 85 km/h Estimated speed loss after drop: 41 km/h 249 kg General Purpose Bomb SC 250 Additional mass: 279 kg Ammunition mass: 249 kg Racks mass: 30 kg Estimated speed loss before drop: 37 km/h Estimated speed loss after drop: 11 km/h 500 kg General Purpose Bomb SC 500 Additional mass: 530 kg Ammunition mass: 500 kg Racks mass: 30 kg Estimated speed loss before drop: 43 km/h Estimated speed loss after drop: 13 km/h Operation features: - Airplane has a wide automatization of the engine systems, in fact, to control speed it is only necessary to use the throttle lever. There is no need to manually set engine revolutions and mixture or supercharger gear in normal flight. The engine supercharger has an automatic switch system which depends on altitude and engine revolutions. - To reduce swinging during taxiing due to prop-wash the propeller pitch control should be switched to manual mode and pitch should be reduced to minimum. - When the angle of attack increases to critical levels the wing may stall suddenly and unexpectedly. There is almost no pre-stall buffet before the stalling. To avoid this the pilot must pay additional attention when performing extreme maneuvering. - Airplane has no flight-control trimmers. Airplane is equipped with bendable trim tabs that can be set pre-flight by ground personnel. - Airplane has a manually controlled horizontal stabilizer which is electrically-actuated. It should be set to +1.5° before takeoff and landing. Also, it may be used to trim the flight stick during the flight. In a deep dive the stabilizer should be set so that the pilot must push the flight stick forward to maintain the dive angle. - Airplane has electrically-actuated landing flaps with three fixed positions: retracted, takeoff (13°) and landing (58°). Flaps control buttons and indicator lights are located on left panel near the throttle. The flap angle may also be checked by indicators on the left and right wing outside the cockpit. - Airplane has a tail wheel lock system which locks the tail wheel if the flight-stick is pulled backward. The tailwheel should be locked when taxiing straight for a long distance, before takeoff and after touchdown upon landing. - Airplane has independent left and right hydraulic wheel brake controls. To apply either brake push the upper part of the rudder pedal. - Airplane has a fuel gauge which shows the amount of remaining fuel in the front or rear fuel tank depending on switch position. In game the fuel indicator switch changes by itself during horizontal flight by every 10 seconds. Also, the airplane has an emergency fuel warning light (100 liters). - It is impossible to open or close the canopy at high speed due to strong airflow. The canopy has an emergency release system for bailouts. - The control system for the bomb rack only allows for dropping bombs one by one. - The gunsight has a sliding sun-filter. Fw 190 D-9 Indicated stall speed in flight configuration: 174..197 km/h Indicated stall speed in takeoff/landing configuration: 160..181 km/h Dive speed limit: 850 km/h Maximum load factor: 11 G Stall angle of attack in flight configuration: 19.5° Stall angle of attack in landing configuration: 18.1° Maximum true air speed at sea level, engine mode - Emergency: 607 km/h Maximum true air speed at 2000 m, engine mode - Emergency: 641 km/h Maximum true air speed at 5200 m, engine mode - Emergency: 694 km/h Maximum true air speed at sea level, engine mode - Combat: 565 km/h Maximum true air speed at 3200 m, engine mode - Combat: 623 km/h Maximum true air speed at 6500 m, engine mode - Combat: 663 km/h Service ceiling: 11600 m Climb rate at sea level: 19.0 m/s Climb rate at 3000 m: 17.3 m/s Climb rate at 6000 m: 14.6 m/s Maximum performance turn at sea level: 20.0 s, at 300 km/h IAS. Maximum performance turn at 3000 m: 29.0 s, at 300 km/h IAS. Flight endurance at 3000 m: 2.5 h, at 350 km/h IAS. Takeoff speed: 180..220 km/h Glideslope speed: 215..225 km/h Landing speed: 160..180 km/h Landing angle: 12.5° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates are given for Combat power, turn times are given for Emergency power. Engine: Model: Jumo-213 A1 Maximum power in Emergency mode at sea level: 2130 HP Maximum power in Emergency mode at 3800 m: 1980 HP Maximum power in Combat mode at sea level: 1900 HP Maximum power in Combat mode at 5100 m: 1680 HP Engine modes: Nominal (unlimited time): 3000 RPM, 1.42 ata Combat power (up to 30 minutes): 3250 RPM, 1.51 ata Emergency power (up to 3 minutes): 3250 RPM, 1.7 ata Emergency power with MW-50 (up to 10 minutes): 3250 RPM, 1.8 ata Water rated temperature in engine output: 55..100 °C Water maximum temperature in engine output: 110 °C Oil rated temperature in engine output: 40..110 °C Oil maximum temperature in engine output: 120 °C Supercharger gear shift altitude: automatic Empty weight: 3443 kg Minimum weight (no ammo, 10% fuel): 3759 kg Standard weight: 4289 kg Maximum takeoff weight: 4832 kg Fuel load: 388 kg / 524 l Useful load: 1389 kg Forward-firing armament: 2 x 20mm gun "MG 151/20", 250 rounds, 700 rounds per minute, wing-mounted 2 x 13mm machine gun "MG 131", 475 rounds, 900 rounds per minute, synchronized Bombs: Up to 4 x 66 kg fragmentation bombs "SD 70" 249 kg general purpose bomb "SC 250" 500 kg general purpose bomb "SC 500" Rockets: Two WGr.21 rockets in jettisonable launchers 26 R4M rockets Length: 10.2 m Wingspan: 10.51 m Wing surface: 18.3 m² Combat debut: end of September 1944 Additional airplane configurations list: 4 x 66 kg fragmentation bombs SD 70 Additional mass: 324 kg Ammunition mass: 264 kg Racks mass: 60 kg Estimated speed loss before drop: 61 km/h Estimated speed loss after drop: 13 km/h249 kg General Purpose Bomb SC 250 Additional mass: 279 kg Ammunition mass: 249 kg Racks mass: 30 kg Estimated speed loss before drop: 31 km/h Estimated speed loss after drop: 6 km/h500 kg General Purpose Bomb SC 500 Additional mass: 530 kg Ammunition mass: 500 kg Racks mass: 30 kg Estimated speed loss before drop: 35 km/h Estimated speed loss after drop: 6 km/h2 x WGr.21 rockets in jettisonable launchers Additional mass: 258 kg Ammunition mass: 224 kg Racks mass: 34 kg Estimated speed loss before launch: 58 km/h Estimated speed loss after launch: 12 km/h Estimated speed loss after drop: 1 km/h26 x 55 mm High Explosive unguided rockets R4M Additional mass: 107 kg Ammunition mass: 87 kg Racks mass: 20 kg Estimated speed loss before launch: 24 km/h Estimated speed loss after launch: 14 km/hEZ42 Gyro Gunsight Additional mass: 13 kg Estimated speed loss: 0 km/hBubble Canopy Additional mass: 3 kg Estimated speed loss: 1 km/h Operation features: - Airplane has a wide automatization of the engine systems, in fact, to control speed it is only necessary to use the throttle lever. There is no need to manually set engine revolutions and mixture or supercharger gear in normal flight. The engine supercharger has an automatic switch system which depends on altitude and engine revolutions. - The aircraft is equipped with MW-50 water-methanol mixture injection system that prevents the engine detonation in the emergency power mode. - Radiator flaps are controlled automatically, keeping a set coolant temperature. This temperature can be set by a pilot using the thermostat regulator if needed (default 0% setting is adequate for all engine modes, while increasing it cools the engine more). - When the angle of attack increases to critical levels the wing may stall suddenly and unexpectedly. There is almost no pre-stall buffet before the stalling. To avoid this the pilot must pay additional attention when performing extreme maneuvering. - Airplane has no flight-control trimmers. Airplane is equipped with bendable trim tabs that can be set pre-flight by ground personnel. - Airplane has a manually controlled horizontal stabilizer which is electrically-actuated. It should be set to +1.5° before takeoff and landing. Also, it may be used to trim the flight stick during the flight. In a deep dive the stabilizer should be set so that the pilot must push the flight stick forward to maintain the dive angle. - Airplane has electrically-actuated landing flaps with three fixed positions: retracted, takeoff (13°) and landing (58°). Flaps control buttons are located on left panel near the throttle. The flap angle may be checked by indicators on the left and right wing outside the cockpit. - Airplane has a tail wheel lock system which locks the tail wheel if the flight-stick is pulled backward. The tailwheel should be locked when taxiing straight for a long distance, before takeoff and after touchdown upon landing. - Airplane has independent left and right hydraulic wheel brake controls. To apply either brake push the upper part of the rudder pedal. - Airplane has a fuel gauge which shows the amount of remaining fuel in the front or rear fuel tank depending on switch position. In game the fuel indicator switch changes by itself during horizontal flight by every 10 seconds. Also, the airplane has an emergency fuel warning light (100 liters). - It is impossible to open or close the canopy at high speed due to strong airflow. The canopy has an emergency release system for bailouts. - The standard bomb release controller allows dropping the bombs only one by one. - The gunsight has a sliding sun-filter. MC.202 series VIII Indicated stall speed in flight configuration: 151..166 km/h Indicated stall speed in takeoff/landing configuration: 139..152 km/h Dive speed limit: 850 km/h Maximum load factor: 14.8 G Stall angle of attack in flight configuration: 19.6 ° Stall angle of attack in landing configuration: 17.4 ° Maximum true air speed at sea level, engine mode - Combat: 500 km/h Maximum true air speed at 2000 m, engine mode - Combat: 543 km/h Maximum true air speed at 5000 m, engine mode - Combat: 604 km/h Service ceiling: 11300 m Climb rate at sea level: 17.3 m/s Climb rate at 3000 m: 15.1 m/s Climb rate at 6000 m: 10.6 m/s Maximum performance turn at sea level: 22.6 s, at 270 km/h IAS. Maximum performance turn at 3000 m: 28.2 s, at 270 km/h IAS. Flight endurance at 3000 m: 2.2 h, at 350 km/h IAS. Takeoff speed: 160..190 km/h Glideslope speed: 190..200 km/h Landing speed: 140..150 km/h Landing angle: 13.9 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates are given for Combat power, turn times are given for Boosted power. Engine: Model: RA.1000 Maximum power in Boosted mode at sea level: 1175 HP Maximum power in Combat mode at sea level: 1050 HP Maximum power in Combat mode at 3700 m: 1100 HP Engine modes: Nominal (unlimited time): 2200 RPM, 1.23 ata Combat power (up to 5 minutes): 2400 RPM, 1.35 ata Boosted power (up to 1 minute): 2500 RPM, 1.45 ata Water rated temperature in engine intake: 70..80 °C Water rated temperature in engine output: 94 °C Water maximum temperature in engine output: 100 °C Oil rated temperature in engine intake: 60..75 °C Oil maximum temperature in engine intake: 85 °C Oil rated temperature in engine output: 90..100 °C Oil maximum temperature in engine output: 110 °C Supercharger gear shift altitude: fluid coupling Empty weight: 2448 kg Minimum weight (no ammo, 10% fuel): 2622 kg Standard weight: 2967 kg Maximum takeoff weight: 3197 kg Fuel load: 307 kg / 430 l Useful load: 749 kg Forward-firing armament: 2 x 12.7mm machine gun "Breda SAFAT 12.7", 400 rounds, 700 rounds per minute, synchronized 2 x 7.7mm machine gun "Breda SAFAT 7.7", 500 rounds, 900 rounds per minute, wing-mounted (modification) 2 x 20mm gun "MG 151/20", 135 rounds, 700 rounds per minute, wing-mounted (modification) Bombs: 2 x 50 kg general purpose bombs "50-T" 2 x 100 kg general purpose bombs "100-T" Length: 8.85 m Wingspan: 10.58 m Wing surface: 16.8 m^2 Combat debut: June 1942 Additional airplane configurations list: Breda SAFAT 7.7mm wing-mounted machineguns with 500 rounds per each Additional mass: 49 kg Ammunition mass: 24 kg Guns mass: 25 kg Estimated speed loss: 0 km/h MG 151/20 20mm guns in wing-mounted gun pods with 135 rounds per each Additional mass: 212 kg Ammunition mass: 55 kg Guns mass: 157 kg Estimated speed loss: 15 km/h 2 x 55 kg General Purpose Bombs 50-T Additional mass: 130 kg Ammunition mass: 110 kg Racks mass: 20 kg Estimated speed loss before drop: 14 km/h Estimated speed loss after drop: 7 km/h 100 kg General Purpose Bomb 100-T Additional mass: 220 kg Ammunition mass: 200 kg Racks mass: 20 kg Estimated speed loss before drop: 20 km/h Estimated speed loss after drop: 7 km/h Additional pilot protection: armoured triplex wind screen Additional mass: 10 kg Estimated speed loss: 0 km/h Operation features: - Throttle lever is inverted: backward = full throttle, forward = idle throttle. - Engine is equipped with automatic mixture control system and supercharger with fluid coupling which does not requiring manual control. - Engine RPM has an automatic governor with two fixed modes: 2200 RPM - normal mode, 2400 RPM - boosted mode. Also, it is possible to turn off the governor and control the propeller pitch manually by mechanical actuator. - Water and oil radiator shutter control is manual. - Airplane has no flight-control trimmers. Airplane is equipped with bendable trim tabs that can be set pre-flight by ground personnel. - Airplane has asymmetric half-wings for roll-compensation: the left one is 20 cm longer than right one. - Airplane has a manually controlled horizontal stabilizer. It should be set to neutral before takeoff and landing. Also, it may be used to trim the flight stick during the flight. In a deep dive the stabilizer should be set so that the pilot must push the flight stick forward to maintain the dive angle. - Landing flaps have a hydraulic actuator and they can be extended to any angle up to 45°. The flap system includes a "pneumatic spring" which allows flaps to be pressed upwards by airflow at airspeed more than 200 km/h. - Airplane has a manual tail wheel lock. Wheel should be locked when taxiing straight for a long distance and before takeoff and landing. - Airplane has differential pneumatic wheel brakes with shared control lever. This means that if the brake lever is held and the rudder pedal the opposite wheel brake is gradually released causing the plane to swing to one side or the other. - Airplane has a fuel gauge which indicates only the front fuel tank level. - The design of the cockpit canopy does not allow it to be opened during flight. The canopy should be closed before takeoff to prevent damage. The canopy has an emergency release system for bailouts. - The control system of wing-mounted bomb racks only allows the dropping of bombs one by one. - The gunsight has a sliding sun-filter. There is also a back-up folding mechanical sight which can be used if main sight is damaged. Hs 129 B-2 Indicated stall speed in flight configuration: 143..159 km/h Indicated stall speed in takeoff/landing configuration: 136..150 km/h Dive speed limit: 670 km/h Maximum load factor: 9 G Stall angle of attack in flight configuration: 20.0 ° Stall angle of attack in landing configuration: 18.0 ° Maximum true air speed at sea level, engine mode - Combat: 349 km/h Maximum true air speed at 3000 m, engine mode - Combat: 396 km/h Service ceiling: 7000 m Climb rate at sea level: 8.4 m/s Climb rate at 3000 m: 8.1 m/s Climb rate at 6000 m: 2.6 m/s Maximum performance turn at sea level: 30.0 s, at 255 km/h IAS. Maximum performance turn at 3000 m: 46.0 s, at 270 km/h IAS. Flight endurance at 3000 m: 2.1 h, at 300 km/h IAS. Takeoff speed: 145..155 km/h Glideslope speed: 180..200 km/h Landing speed: 135..145 km/h Landing angle: 10.6 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates and turn times are given for Combat power. Engine: Model: Gnome-Rhone 14 M Maximum power in Take-off mode at sea level: 700 HP Maximum power in Combat mode at sea level: 580 HP Maximum power in Combat mode at 4000 m: 650 HP Engine modes: Nominal (unlimited time): 2350 RPM, 1.1 ata Combat power (up to 30 minutes): 2750 RPM, 1.25 ata Take-off power (up to 1 minute): 3030 RPM, 1.5 ata Oil rated temperature in engine intake: 60..75 °C Oil maximum temperature in engine intake: 125 °C Supercharger gear shift altitude: single gear Empty weight: 3992 kg Minimum weight (no ammo, 10% fuel): 4200 kg Standart weight: 4756 kg Maximum takeoff weight: 5170 kg Fuel load: 451 kg / 610 l Useful load: 1178 kg Forward-firing armament: 2 x 7.92mm machine gun "MG 17", 1000 rounds, 1200 rounds per minute, nose-mounted 2 x 20mm gun "MG 151/15", 250 rounds, 700 rounds per minute, nose-mounted 2 x 20mm gun "MG 151/20", 250 rounds, 700 rounds per minute, nose-mounted (modification) 4 x 7.92mm machine gun "MG 17", 1000 rounds, 1200 rounds per minute, underbelly (modification) 30mm gun "MK 101", 30 rounds, 250 rounds per minute, underbelly (modification) 30mm gun "MK 103", 80 rounds, 400 rounds per minute, underbelly (modification) Bombs: Up to 6 x 55 kg general purpose bombs "SC 50" 249 kg general purpose bombs "SC 250" Length: 9.7 m Wingspan: 14.2 m Wing surface: 28.9 m^2 Combat debut: May 1942 Additional airplane configurations list: 2 x MG 151/20 20mm nose-gun with 250 rounds per each Additional mass: 14.4 kg Ammunition mass: 105 kg Gun mass: 42 kg Estimated speed loss: 0 km/h Four MG 17 7.92mm machineguns in fuselage mounted gun pod with 1000 rounds per each Additional mass: 194.8 kg Ammunition mass: 106 kg Guns mass: 88.8 kg Estimated speed loss: 4 km/h 30mm MK 101 autocannon gun pod with 30 rounds Additional mass: 179 kg Ammunition mass: 24 kg Guns mass: 155 kg Estimated speed loss: 6 km/h 30mm MK 103 autocannon gun pod with 80 rounds Additional mass: 234.2 kg Ammunition mass: 74.7 kg Guns mass: 159.5 kg Estimated speed loss: 6km/h Peilrahmen PR 16 fixed loop radio compass for navigation with radio beacons Additional mass: 10 kg Estimated speed loss: 0 km/h Rear view mirror Additional mass: 1 kg Estimated speed loss: 1 km/h Operation features: - Controlling the propellers RPM is possible only in the manual mode by changing the propeller pitch. The automatic mode keeps the RPM at 2750. - The engine control lever allows setting the pressure up to the combat mode (1.25 ATA). - To switch the engines to the take-off mode, move the boost lever to 1.5 ATA position and set the propellers to 3030 RPM. - Engine mixture control is automatic. Leaning the mixture manually reduces the fuel consumption during flight. - The oil radiator shutters are controlled automatically and don't have a manual mode. - The propellers have a feathering system which should be activated in case of engine damage to reduce drag of the propeller in auto-rotation. - The aircraft has only pitch and yaw flight-control trimmers. - The aircraft has independent left and right hydraulic wheel brake controls. To apply either brake push the upper part of the rudder pedal. - Landing flaps have a hydraulic actuator and they can be extended to any angle up to 40° or to the fixed take-off position. - The tail wheel rotates freely and does not have a lock. For this reason, it is necessary to confidently and accurately operate the rudder pedals during the takeoff and landing. - The aircraft fuel gauges are positioned directly on the engine nacelles and show only the amount of fuel remaining in the wing tanks (the fuel remaining in the central fuel tank is not indicated). - The aircraft isn't equipped with an oxygen supply system, so flying above 4000 meters is forbidden. - The aircraft is equipped with an electric bomb release controller that allows dropping the bombs only one by one. - The gunsight has a sliding sun-filter. Ju 52/3m g4e Indicated stall speed in flight configuration: 105..117 km/h Indicated stall speed in takeoff/landing configuration: 92..109 km/h Dive speed limit: 330 km/h Maximum load factor: 4.0 G Stall angle of attack in flight configuration: 20 ° Stall angle of attack in landing configuration: 17.2 ° Maximum true air speed at sea level, engine mode - Climb: 260 km/h Maximum true air speed at 3000 m, engine mode - Climb: 258 km/h Maximum true air speed at 6000 m, engine mode - Climb: 241 km/h Service ceiling: 6800 m Climb rate at sea level: 6.9 m/s Climb rate at 3000 m: 4.2 m/s Climb rate at 6000 m: 1.4 m/s Maximum performance turn at sea level: 24.0 s, at 165 km/h IAS. Maximum performance turn at 3000 m: 35.4 s, at 165 km/h IAS. Flight endurance at 3000 m: 5.3 h, at 205 km/h IAS. Takeoff speed: 100..120 km/h Glideslope speed: 140..155 km/h Landing speed: 95..110 km/h Landing angle: 11.7 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates are given for Climb power, turn times are given for Take-off power. Engine: Model: BMW-132a Maximum power in Take-off mode at sea level: 640 HP Maximum power in Take-off mode at 900 m: 660 HP Maximum power in Climb mode at sea level: 575 HP Maximum power in Climb mode at 900 m: 590 HP Engine modes: Nominal (unlimited time): 1925 RPM Climb power (up to 30 minutes): 1975 RPM Take-off power (up to 5 minutes): 2050 RPM Oil rated temperature in engine intake: 60 °C Oil maximum temperature in engine intake: 80 °C Oil rated temperature in engine output: 80 °C Oil maximum temperature in engine output: 100 °C Empty weight: 6305 kg Minimum weight (no ammo, 10% fuel): 7017 kg Standard weight: 10003 kg Maximum takeoff weight: 11333 kg Fuel load: 1824 kg / 2400 l Useful load: 5028 kg Defensive armament: Top: 7.92mm machine gun "MG 15", 1125 rounds, 1000 rounds per minute Length: 18.9 m Wingspan: 29.25 m Wing surface: 111.5 m^2 Combat debut: 1936 Additional airplane configurations list: 2300 kg of military cargo payload Additional mass: 2300 kg Estimated speed loss: 2 km/h 10 x 250 kg drop transport container with parachute MAB 250 Additional mass: 2550 kg Containers mass: 2500 kg Racks mass: 50 kg Estimated speed loss before drop: 2 km/h Estimated speed loss after drop: 0 km/h 12 paratroopers with ammunition Additional mass: 1200 kg Estimated speed loss before drop: 2 km/h Estimated speed loss after drop: 0 km/h Rear turret with MG 15 7.92mm machinegun with 1125 rounds Additional mass: 130 kg Estimated speed loss: 4 km/h Operation features: - Engine has a single stage mechanical supercharger which does not require manual control. - Engine mixture control is manual; it is necessary to lean the mixture if altitude is more than 1 km for optimal engine operation. Also, leaning the mixture allows a reduction in fuel consumption during flight. - All three propellers are fixed pitch ones, so thrust can only be controlled by adjusting the engines throttle (from idle at 25% to maximum power at 100%). 0 - 20% throttle range is used for braking the landing gear wheels. Engine modes can be determined only by watching the engine RPM gauges. - Radiator bypass valve and engine cowls are controlled manually. - Pedals in the cabin are equipped with adjustable load feel mechanism to reduce the pilot's work load. - Airplane has a manually controlled horizontal stabilizer. It should be set to 0° before takeoff, to +2° during flight and to -1.5° for landing. Also, it may be used to trim the flight stick during the flight. - The mechanical flaps control system can be controlled simultaneously with the horizontal stabilizer, these two systems can be linked or unlinked (by using flaps control buttons). It is important to note that it is possible to render the system inoperable so it would not be able to control either the stabilizer or the flaps by deviating from a standard control procedure described below. - Before taking off, set the stabilizer to flight position +2°, engage the link and then move the stabilizer to take-off position 0° - flaps will be extended to 25°. - When airborne, move the stabilizer back to flight position (flaps should also fully retract) and unlink these controls. - Before landing, set the stabilizer to flight position +2°, engage the link and then move the stabilizer to landing position -1.5° - flaps will be fully extended to 40°. - Airplane tail wheel rotates freely and does not have a lock. For this reason, it is necessary to confidently and accurately operate the rudder pedals during the takeoff and landing. - Airplane has separate pneumatic wheel brakes. To brake left or right wheels, move their corresponding left or right engine throttle to 20% or less. Setting the central engine throttle to 20% or less will brake both wheels. Maximum braking efficiency can be achieved by moving the trottle all the way down. In the sim, you can also use the brake buttons to move left and right engine throttles to braking position. - Airplane is equipped with a hydraulic tail wheel parking brake system. - Airplane is equipped with two mechanical fuel float level gauges for left and right fuel tank groups, located on the left and right engine nacelles outside the cabin. - Airplane has three mechanical oil float level gauges on each of the three engine nacelles outside the cabin. - Cargo unload doors can be opened on the ground only. - The left passenger door must be removed before flight for dropping paratroopers or cargo containers. Use the bomb drop button ("B" by default) to drop them. Yak-9 ser.1 Indicated stall speed in flight configuration: 152..160 km/h Indicated stall speed in takeoff/landing configuration: 136..141 km/h Dive speed limit: 750 km/h Maximum load factor: 10.5 G Stall angle of attack in flight configuration: 18° Stall angle of attack in landing configuration: 16° Maximum true air speed at sea level, engine mode - Nominal, 2550 RPM: 537 km/h Maximum true air speed at sea level, engine mode - Nominal, 2700 RPM: 529 km/h Maximum true air speed at 1700 m, engine mode - Nominal, 2700 RPM: 563 km/h Maximum true air speed at 3800 m, engine mode - Nominal, 2700 RPM: 594 km/h Service ceiling: 10500 m Climb rate at sea level: 18.5 m/s Climb rate at 3000 m: 15.8 m/s Climb rate at 6000 m: 9.0 m/s Maximum performance turn at sea level: 17.5 s, at 270 km/h IAS. Maximum performance turn at 3000 m: 22.5 s, at 285 km/h IAS. Flight endurance at 3000 m: 2.1 h, at 350 km/h IAS. Takeoff speed: 160..190 km/h Glideslope speed: 195..205 km/h Landing speed: 135..145 km/h Landing angle: 12 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates and turn times are given for Nominal (2700 RPM) power. Engine: Model: M-105PF Maximum power in Nominal mode (2550 RPM) at sea level: 1240 HP Maximum power in Nominal mode (2700 RPM) at sea level: 1210 HP Maximum power in Nominal mode (2700 RPM) at 800 m: 1260 HP Maximum power in Nominal mode (2700 RPM) at 2700 m: 1200 HP Engine modes: Nominal (unlimited time): 2550/2700 RPM, 1050 mm Hg Water rated temperature in engine output: 70..85 °C Water maximum temperature in engine output: 100 °C Oil rated temperature in engine output: 90..100 °C Oil maximum temperature in engine output: 115 °C Supercharger gear shift altitude: 2200 m Empty weight: 2254 kg Minimum weight (no ammo, 10%25 fuel): 2549 kg Standard weight: 2841 kg Maximum takeoff weight: 2858 kg Fuel load: 324 kg / 440 l Useful load: 604 kg Forward-firing armament: 20mm gun "SsVAK", 120 rounds, 800 rounds per minute, nose-mounted 12.7mm machine gun "UB", 200 rounds, 1000 rounds per minute, synchronized Length: 8.5 m Wingspan: 10 m Wing surface: 17.15 m² Combat debut: November 1942 Additional airplane configurations list: Landing light for night flights Additional mass: 2 kg Estimated speed loss: 0 km/h Rear view mirror Additional mass: 1 kg Estimated speed loss: 0 km/h PBP-1A reflector gunsight Additional mass: 0.5 kg Estimated speed loss: 0 km/h Fixed loop radio compass for navigation with radio beacons Additional mass: 10 kg Estimated speed loss: 0 km/h Operation features: - Engine has a two-stage mechanical supercharger which must be manually switched at 2000...2400m altitude. - Engine mixture control is manual; it is necessary to lean the mixture if altitude is more than 3-4 km for optimal engine operation. Also, leaning the mixture allows a reduction in fuel consumption during flight. - Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM. - Water and oil radiator shutters are controlled manually. - The airplane can only be trimmed in the pitch axis. - Landing flaps have a pneumatic actuator. Flaps can only be fully extended; gradual extending is impossible. Due to the weak force of the actuator the extended landing flaps may be pressed upwards by the airflow if the airspeed is more than 220 km/h. Remember that the flaps will not extend fully in case of high speed. In case of a high-speed landing approach the flaps may extend a few steps further right before landing. - Airplane has a manual control for the tailwheel lock. The unlocked tailwheel has a 90° turn limit. The tailwheel should be locked when taxiing straight for a long distance and before takeoff and landing. - Airplane has differential pneumatic wheel brakes with shared control lever. This means that if the brake lever is held and the rudder pedal the opposite wheel brake is gradually released causing the plane to swing to one side or the other. - Fuel gauges are installed on left and right wing fuel tanks, outside of the cockpit. Less than 25l of fuel remaining in the wing tanks or the central feeder tank (10 litres capacity) are not measured. - The canopy has no emergency release. In order to bail out, you must slow below 550 kph to open the canopy. Yak-9T ser.1 Indicated stall speed in flight configuration: 157..165 km/h Indicated stall speed in takeoff/landing configuration: 139..145 km/h Dive speed limit: 750 km/h Maximum load factor: 10.5 G Stall angle of attack in flight configuration: 18° Stall angle of attack in landing configuration: 16° Maximum true air speed at sea level, engine mode - Nominal, 2550 RPM: 535 km/h Maximum true air speed at sea level, engine mode - Nominal, 2700 RPM: 529 km/h Maximum true air speed at 1850 m, engine mode - Nominal, 2700 RPM: 560 km/h Maximum true air speed at 4000 m, engine mode - Nominal, 2700 RPM: 593 km/h Service ceiling: 10250 m Climb rate at sea level: 16.5 m/s Climb rate at 3000 m: 13.5 m/s Climb rate at 6000 m: 7.5 m/s Maximum performance turn at sea level: 19.0 s, at 270 km/h IAS. Maximum performance turn at 3000 m: 25.5 s, at 285 km/h IAS. Flight endurance at 3000 m: 2.1 h, at 350 km/h IAS. Takeoff speed: 170..200 km/h Glideslope speed: 195..205 km/h Landing speed: 140..150 km/h Landing angle: 12 ° Note 1: the data provided is for international standard atmosphere (ISA). Note 2: flight performance ranges are given for possible aircraft mass ranges. Note 3: maximum speeds, climb rates and turn times are given for standard aircraft mass. Note 4: climb rates and turn times are given for Nominal (2700 RPM) power. Engine: Model: M-105PF Maximum power in Nominal mode (2550 RPM) at sea level: 1240 HP Maximum power in Nominal mode (2700 RPM) at sea level: 1210 HP Maximum power in Nominal mode (2700 RPM) at 800 m: 1260 HP Maximum power in Nominal mode (2700 RPM) at 2700 m: 1200 HP Engine modes: Nominal (unlimited time): 2550/2700 RPM, 1050 mm Hg Water rated temperature in engine output: 70..85 °C Water maximum temperature in engine output: 100 °C Oil rated temperature in engine output: 90..100 °C Oil maximum temperature in engine output: 115 °C Supercharger gear shift altitude: 2200 m Empty weight: 2470 kg Minimum weight (no ammo, 10%25 fuel): 2631 kg Standard weight: 3015 kg Maximum takeoff weight: 3033 kg Fuel load: 316 kg / 430 l Useful load: 563 kg Forward-firing armament: 37mm gun "NS-37", 30 rounds, 250 rounds per minute, nose-mounted 12.7mm machine gun "UB", 200 rounds, 1000 rounds per minute, synchronized Length: 8.5 m Wingspan: 10 m Wing surface: 17.15 m² Combat debut: Summer 1943 Additional airplane configurations list: NS-37 gun ammo counter Additional mass: 1 kg Estimated speed loss: 0 km/h Landing light for night flights Additional mass: 2 kg Estimated speed loss: 0 km/h Rear view mirror Additional mass: 1 kg Estimated speed loss: 0 km/h PBP-1A reflector gunsight Additional mass: 0.5 kg Estimated speed loss: 0 km/h Fixed loop radio compass for navigation with radio beacons Additional mass: 10 kg Estimated speed loss: 0 km/h Operation features: - Engine has a two-stage mechanical supercharger which must be manually switched at 2000...2400m altitude. - Engine mixture control is manual; it is necessary to lean the mixture if altitude is more than 3-4 km for optimal engine operation. Also, leaning the mixture allows a reduction in fuel consumption during flight. - Engine RPM has an automatic governor and it is maintained at the required RPM corresponding to the governor control lever position. The governor automatically controls the propeller pitch to maintain the required RPM. - Water and oil radiator shutters are controlled manually. - The airplane can only be trimmed in the pitch axis. - Landing flaps have a pneumatic actuator. Flaps can only be fully extended; gradual extending is impossible. Due to the weak force of the actuator the extended landing flaps may be pressed upwards by the airflow if the airspeed is more than 220 km/h. Remember that the flaps will not extend fully in case of high speed. In case of a high-speed landing approach the flaps may extend a few steps further right before landing. - Airplane has a manual control for the tailwheel lock. The unlocked tailwheel has a 90° turn limit. The tailwheel should be locked when taxiing straight for a long distance and before takeoff and landing. - Airplane has differential pneumatic wheel brakes with shared control lever. This means that if the brake lever is held and the rudder pedal the opposite wheel brake is gradually released causing the plane to swing to one side or the other. - Fuel gauges are installed on left and right wing fuel tanks, outside of the cockpit. - The canopy has no emergency release. In order to bail out, you must slow below 550 kph to open the canopy. Note: Data in this thread is updating in cases when something was changed in game. Last update: April 27, 2021. Actual for version 4.601. 14 18 73 Link to post Share on other sites
1CGS Han 20714 Posted December 4, 2019 Author 1CGS Share Posted December 4, 2019 Data was updated - all airplanes of "Battle of Bodenplatte" and "Flying Circus" were added, new collector planes were added too. 11 13 3 Link to post Share on other sites
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