Calculate the stagnation pressure and temperature

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Reference no: EM13712185

Air flows isentropic ally at the rate of 0.5 kg/s through a supersonic convergent-divergent nozzle. At the inlet, the pressure is 680 kPa. the temperature 295 K. and the area is 6.5cm^2. If the exit area is 13 cm*2, calculate:

a) The Stagnation pressure and temperature.

b) The exit Mach number

c) The exit pressure and Temperature

d) The area and the verlocity at the throat.

Reference no: EM13712185

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