Engineering, 12.08.2019 19:10, fatty18

Required information an airplane has a mass of 48,000 kg, a wing area of 300 m2, a maximum lift coefficient of 3.2, and a cruising drag coefficient of 0.03 at an altitude of 12,000 m. take the density of standard air as ρ1 = 1.225 kg/m3 at sea level and ρ2 = 0.312 kg/m3 at 12,000 m altitude. determine the safe takeoff speed at sea level, assuming it is 20 percent over the stall speed. the safe takeoff speed at sea level is km/h.

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Required information an airplane has a mass of 48,000 kg, a wing area of 300 m2, a maximum lift coef...