The total drag coefficient for an airplane wing is C0 = C00 + Cf 1-rr A, where C00 is
Chapter 11, Problem 11.68(choose chapter or problem)
The total drag coefficient for an airplane wing is C0 = C00 + Cf 1-rr A, where C00 is the form drag coefficient, CL is the lift coefficient and A is the aspect ratio of the wing. The power is given by P = F0 V = l/2 CoP V3 S. For level flight the lift is equal to the weight, so W/S = l/2pCL V2 , where W/S is called the "wing loading: Find an expression for V for which the power is a minimum in terms ofVMmPow
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