An engineer needs a value of lift force for an airplane that has a coefficient of lift

Chapter 8, Problem 8.39

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An engineer needs a value of lift force for an airplane that has a coefficient of lift (Cd of 0.4. The 1r-group is defined as Ft CL = 2-- pV2S where FL is the lift force, p is the density of an1bient air, Vis the speed of the air relative to the airplane, and S is the area of the wings from a top view. Estimate the lift force in newtons for a speed of 80 m/s, an air density of 1.1 kg/m3 , and a wing area (planform area) of 15m2 .

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