Originally Posted by
Virtually There
As far as I'm aware, ailerons (not flaperons) do not change the lift coefficient of the wing in the same manner flaps do. In addition, there seems to be a bit of confusion about the reference point of AoA in relation to flaps. Flaps change the chord line, so if you do not alter the point of reference of AoA for a clean wing, then of course the AoA of the wing as a whole will decrease. But the stalling AoA of the chord line in reference to the relative airflow is still the same.
nope
A simple aileron is just like a simple flap as far as the aerodynamics of the aerofoil is concerned.
Airflow separation results from adverse pressure gradient. Deflecting that flap or aileron increases the negative Cp near the leading edge therefore that adverse pressure gradient will increase so ....
Someone kindly provided the usual charts from wind tunnel data where we retain the chord line of the aerofoil with nil flap or control surface deflection. That is my usual reference.
Some calculations we do are via the so-called thin aerofoil theory where we change the chord line to follow the deflected trailing edge. A fine theory but generally doesn't lead us to a calculation of stalling angle of attack, at least not a realistic one.