An engineer needs a value of lift force for an airplane that has a coefficient of lift (CL) of 0.4. The π-group is defined asWhere F_L is the lift force, ρ is the density of ambient air, V is 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 90 m/s, an air density of 1.1 kg/m³, and a wing area (planform area) of 18 m².

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FL C = 2- pV's