Question

Is lift loss with increase in angle of attack?

(a) True

(b) False

This question was addressed to me in class test.

I want to ask this question from Viscous Flow in section Incompressible Flow over Airfoils of Aerodynamics

Answer 1

Right choice is (a) True

Explanation: The loss in lift which does the increase in the angle of attack, in most instances stall occurs gradually, with a slow upward motion of the separation of the boundary layer from the trailing edge to the leading edge.