Question

The zero-lift angle of attack for a thin, cambered airfoil increases in magnitude with the increasing camber of the airfoil.

(a) True

(b) False

The question was asked by my school principal while I was bunking the class.

This key question is from The Cambered Airfoil topic in division Incompressible Flow over Airfoils of Aerodynamics

Answer 1

The correct answer is (a) True

To explain I would say: Using the formula for αL=0=\(\frac {-1}{\pi}\int_0^{\pi}\frac {dz}{dx} \)(cos⁡∅-1)d∅, the dependence of the zero-lift angle of attack on camber can be seen. It is clear that for higher cambered airfoils, αL=0 shifts to the negative side.