Question

In the case of cambered airfoil the value of α0 is positive.

(a) True

(b) False

This question was posed to me in my homework.

The query is from Lift Force in section Aircraft Force Systems and the Equations of Motion of Aircraft Performance

Answer 1

Right answer is (b) False

To explain I would say: In the case of cambered airfoil the value of α0 is negative. The zero-lift angle of attack is zero if the aerofoil is symmetric. The zero-lift angle of attack is represented by α0. For symmetric airfoil the α0=0, for asymmetric airfoil the α0≠0.