Cambered wing has minimum drag coefficient of 0.05 and constant K of 0.023. If CL is 0.8 then find the value of CD. Given minimum drag occurs at CL of 0.1.(a) 0.06127(b) 6.1(c) 61.2(d) 0.6721The question was posed to me in class test.The query is from Aerodynamic Coefficients topic in chapter Aerodynamics of Aircraft Design

Cambered wing has minimum drag coefficient of 0.05 and constant K of 0

1.	Cambered wing has minimum drag coefficient of 0.05 and constant K of 0.023. If CL is 0.8 then find the value of CD. Given minimum drag occurs at CL of 0.1.(a) 0.06127(b) 6.1(c) 61.2(d) 0.6721The question was posed to me in class test.The query is from Aerodynamic Coefficients topic in chapter Aerodynamics of Aircraft Design
Answer» Right CHOICE is (a) 0.06127 To elaborate: Given, minimum drag COEFFICIENT CDmin = 0.05, constant K of 0.023, CL is 0.8 and minimum drag OCCURS at CL of 0.1. Hence, CLmindrag = 0.1. Now, CD is given by, CD = CDmin + K(CL – CLmindrag)^2 = 0.05+0.023(0.8-0.1)^2 = 0.06127.

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