If my understanding is correct, an aircraft stalls beyond that AOA
which, when increased any further, produces no (further) lift. If
correct, would it be logical to infer that an aircraft's stalling AOA:
a. is dependent on its airspeed, and is independent of its weight and
weight distribution, and
b. varies, for a given airspeed, with the air density (altitude)
I know these are way elementary, but please help out.
Cheers,
Ramapriya