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Name Name d=0-1 The fuselage of a commercial airliner has an average diameter, D, of 12 feet and a length, L, of 110 feet. The skin friction drag on it can be treated as that on a flat plate with dimensions of D by L feet. The skin friction drag coefficient from equation 11-22 is for incompressible flow. To convert it for compressible flow multiply it by 0.87. The pressure drag coefficient, Cd is 0.9 counts (one count- 0.001). Determine the total drag due to pressure and skin friction and the power required in horsepower to overcome the total drag if the airliner is cruising at M. 0.8 at 39,000 feet (V. 774.36 f/is and p. 6.161 (10)4 sl/f3). Assume the flow is compressible, the absolute viscosity is 3.0(10) sl/s/f and that the transition Reynolds number from laminar to turbulent flow on the airliner is 500,000. There are 550 ft ib/s per HP (horsepower). Solve the problem in the British system of units

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