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

The lift per unit span for a thin, cambered airfoil with α=5°, A0=0.

1.	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
Answer» Correct choice is (a) L’ = cπ\(V_∞^2\)ρ∞ (1.15) Easy EXPLANATION: For a thin CAMBERED AIRFOIL lift per unit SPAN is given by L’ = cπ\(V_∞^2\)ρ∞ (A0+\(\frac {1}{2}\)A1). Thus, with the given value of A0 and A1 we get L’ = cπ\(V_∞^2\)ρ∞ (1.15).

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