For the airplane in Prob. 4.12, the total cross-sectional area of the inlet to the jet engines is 20 ft2. Assume that the flow properties of the air entering the inlet are those of the free stream ahead of the airplane. Fuel is injected inside the engine at a rate of 0.05 lb of fuel for every pound of air flowing through the engine (that is, the fuel-air ratio by mass is 0.05). Calculate the mass flow (in slugs/per second) that comes out the exit of the engine. Prob. 4.12 A supersonic transport is flying at a velocity of 1500 mi1h at a standard altitude of 50,000 ft. The temperature at a point in the flow over the wing is 793.32°R. Calculate the flow velocity at that point.
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