So the LA-5 Fn has more than CLmax 2? Nice...
ANd the AoA topic says " The critical or stalling angle of attack is typically around 15° - 20° for many airfoils. "
So the LA-5 FN is "hold my beer" and I ll be better than avarage?
Fig. Shows the cross section of a wing of a plane.
The axis of the wing shown by dotted line is called chord.
The angle between chord and wind direction is called angle of attack.
The figure also shows the air- stream lines.
The pressure force arising according to Bernoulli's principle is denoted by P.
For a given wind speed, the lift ,P cos ( theta) increases with the angle of attack up to certain limit. Beyond this it starts decreasing .
This limiting value of angle is called stalling angle and it's value varies from about 15 to 20 degree.
Note that L= P cos ( theta) is lift and D=P sin (theta) is drag.
The ratio lift/ drag is maximum when the angle of attack is about 4 degree.
Therefore , we have maximum efficiency of flight at this angle of attack.
Normally, the angle of attack is adjusted between 3 to 6 degree.
So it would be awesome to see the historical sources for tha LA-5 FN.