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An airplane has a mass of 48,000 kg, a wing area of 300 m2, a maximum...

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. Determine(a) the takeoff speed at sea level, assuming it is 20 percent
over the stall speed, and (b) the thrust that the engines must
deliver for a cruising speed of 900 km/h.

Engineering   Mechanical-Engineering   
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