The total drag coefficient for an airplane wing is C D = C D0 + C /πΛ, where C D0 is the form drag coefficient, C L is the lift coeffi cient and Λ is the aspect ratio of the wing. Th e power is given...

The total drag coefficient for an airplane wing is C_D
= C_D0
+ C/πΛ, where C_D0
is the form drag coefficient, C_L
is the lift coeffi cient and Λ is the aspect ratio of the wing. Th e power is given by P = F_DV = 1/2 C_DρV³
S. For level flight the lift is equal to the weight, so W/S = 1/2_ρC_LV², where W/S is called the “wing loading.” Find an expression for V for which the power is a minimum in terms of V Min Power = f (ρ, Λ, W/S, C_D0), and find the V for minimum power when ρ = 1 kg/m³, Λ = 10, W/S = 600 N/m², and C_D
= 0.02.