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LoginThe 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)
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The question is from The Cambered Airfoil topic in portion Incompressible Flow over Airfoils of Aerodynamics
Aerodynamics Incompressible Flow over Airfoils in Aerodynamics 3 years ago
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).
Posted on 02 Dec 2021, this text provides information on Aerodynamics related to Incompressible Flow over Airfoils in Aerodynamics. Please note that while accuracy is prioritized, the data presented might not be entirely correct or up-to-date. This information is offered for general knowledge and informational purposes only, and should not be considered as a substitute for professional advice.
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