Critical angle of attack and stall
I am confused.Again.
According to theory,the critical angle of attack it the angle of attack:
1)where the CL (coefficient of lift) reaches its maximum value,and beyond which it will decrease
2)beyond which the separation point will syddenly move well forward
3)beyond which the center of pressure will suddenly move rearward
4)where the aircraft stalls.
We know that the aircraft stalls when the boundary layer has mostly separated from the wing (breakdown of streamline flow above wing) and there is no sufficient lift.So,due to decreased lift,it will start to sink.
But,the theory says that stall happens at the critical or stalling angle of attack where (as I wrote above) the CL is at its maximum value,and the lift produced at that moment can counteract weight.
So,stall happens at the critical angle of attack of shortly after?
Can anyone help me?
Cheers!