A wing is designed to operate with free stream velocity of 20m/s and air density of 1.225 kg/m^3. Find aerodynamic efficiency of given wing. Consider S as 8 m^2, CL as 0.9 and CD as 1.25.(a) 0.72(b) 2(c) 3(d) 5.23This question was addressed to me in examination.Question is from Aerodynamic Coefficients in section Aerodynamics of Aircraft Design

A wing is designed to operate with free stream velocity of 20m/s and a

1.	A wing is designed to operate with free stream velocity of 20m/s and air density of 1.225 kg/m^3. Find aerodynamic efficiency of given wing. Consider S as 8 m^2, CL as 0.9 and CD as 1.25.(a) 0.72(b) 2(c) 3(d) 5.23This question was addressed to me in examination.Question is from Aerodynamic Coefficients in section Aerodynamics of Aircraft Design
Answer» The correct ANSWER is (a) 0.72 The BEST explanation: Given, CL = 0.9, CD = 1.25 Aerodynamic efficiency is DEFINED as the RATIO of CL and CD of the aircraft. Hence, Aerodynamic efficiency = CL/CD = 0.9/1.25 = 0.72.

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