Question

The coefficient of lift for a thin, cambered airfoil with A0=0.2 and A1=1.12 is____

(a) π1.52

(b) π1

(c) π0.52

(d) π2

The question was posed to me in my homework.

My question comes from The Cambered Airfoil topic in portion Incompressible Flow over Airfoils of Aerodynamics

Answer 1

The correct choice is (a) π1.52

For explanation I would say: The lift coefficient from the thin airfoil theory for a cambered airfoil is given by

cl=π(2A0+A1). So putting A0 and A1 we get cl = π1.52.