What's the pattern of airflow over the airfoil at high angle of attack? When at high angle of attack the boundary layer tends to:
A. stagnate and stop 
B. loop around the upper camber line 
C. decrease air pressure along the chord

The answer is A, but as I see it, B seems like a better answer. What's your opinions?
For your information, the material explains that B is the wrong answer because &quot;As the boundary layer becomes stagnate and stops, the airflow will separate and loop around the upper surface and a stall occurs,&quot; which I don't find satisfying.
The question is about the boundary layer, which indeed stagnates and stops at high AoA, as shown for the laminar boundary layer in the picture. Then the airflow will detach from the upper surface, after the point where the boundary layer has stopped.



B. makes no sense to me, I'm only aware of one camber line.