1. The mass flow of air through a supersonic nozzle is 1.5 lb.,/s. The exit velocity is 1500 , and the reservoir temperature and pressure are 1 000°R and 7 , respectively. Calculate the area of the nozzle exit. For air, Cp = 6000 ft · lb/ (slug)(0R). 2. 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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