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 "As the boundary layer becomes stagnate and stops, the airflow will separate and loop around the upper surface and a stall occurs," which I don't find satisfying.