The lift per unit span for a thin, cambered airfoil with α=5°, A0=0.65, A1=1 is____
(a) L’ = cπ\(V_∞^2\)ρ∞ (1.15)
(b) L’ = cπ\(V_∞^2\)ρ∞ (1.65)
(c) L’ = cπ\(V_∞^2\)ρ∞ (-0.35)
(d) L’ = cπ\(V_∞^2\)ρ∞ (0.15)
This question was addressed to me in a job interview.
The question is from The Cambered Airfoil topic in portion Incompressible Flow over Airfoils of Aerodynamics