The total drag coefficient for an airplane wing is C_D = C_D0 + C²_L/πΛ, where CD0 is the form drag coefficient, C_L is the lift coefficient and Λ is the aspect ratio of the wing. The power is given by P = F_DV = 1/2 C_DρV³S. For level flight the lift is equal to the weight, so W/S = 1/2ρC_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_MinPower = f (ρ, Λ, W/S, C_D0), and fi nd the V for minimum power when ρ = 1 kg/m³, Λ = 10, W/S = 600 N/m², and C_D = 0.02.