Consider an airplane with a wing area of 240 ft2, a span of 44 ft, an Oswald efficiency of 0.75, and a zero-lift drag coefficient of 240 counts (i. e., CD0=0.024). Presume that the airplane is operating at 8,000 ft altitude at a weight of 7,600 lbs.

a. What is the minimum drag in lbs that the aircraft can achieve at this altitude and weight?

b. What is the speed in knots at which this minimum drag occurs?

c. What is the minimum power required in hp that the aircraft can achieve at this altitude and weight?

d. What is the speed in kts at which this minimum power required occurs?

Question

16 June, 07:56

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Kymani Mosley · Answer 1

Drag force=1/2Cd*Area*density*V^2

A=240 ft^2

cd=0.75

Drage force=675 lbs