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Engineering, 18.02.2021 23:40 sailormaries7101

Air flow isentropically through a supersonic convergent divergent nozzle with 0.5 kg/s. At the inlet, the pressure is 680 kPa and the temperature is 295 K, and the area is 6.5 cm2. If the exit area is 13 cm2 calculate: (1 point) a- The stagnation pressure and temperature. b- The exit Mach number. c- The exit pressure and temperature. d- The area and velocity at the throat. e- What will be the corresponding exit Mach number if the flow completely subsonic in the nozzle

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Air flow isentropically through a supersonic convergent divergent nozzle with 0.5 kg/s. At the inlet...
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