The lift per unit span for a thin, cambered airfoil with Γ=10\(\frac {m^2}{s}\), ρ∞=1.0255\(\frac {kg}{m^3}\), V∞=10\(\frac {m}{s}\) is____(a) 0(b) 102.55\(\frac {N}{m}\)(c) 102.55N(d) 55\(\frac {N}{m}\)This question was posed to me during an online exam.My query is from The Cambered Airfoil topic in section Incompressible Flow over Airfoils of Aerodynamics

The lift per unit span for a thin, cambered airfoil with Γ=10\(\frac

1.	The lift per unit span for a thin, cambered airfoil with Γ=10\(\frac {m^2}{s}\), ρ∞=1.0255\(\frac {kg}{m^3}\), V∞=10\(\frac {m}{s}\) is____(a) 0(b) 102.55\(\frac {N}{m}\)(c) 102.55N(d) 55\(\frac {N}{m}\)This question was posed to me during an online exam.My query is from The Cambered Airfoil topic in section Incompressible Flow over Airfoils of Aerodynamics
Answer» The correct OPTION is (a) 0 The best I can explain: The lift PER unit span is GIVEN by the formula L’=Γρ∞V∞ by Kutta-Joukowski Theorem. Putting the RESPECTIVE VALUES given in the question, L’=102.55\(\frac {N}{m}\) (unit is N/m, not N).

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