Find the mach number and the temperature on the nozzle area

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Reference no: EM131467075

Question: Air flows through a convergent-divergent nozzle. The air has Mach 0.50 and a pressure and a temperature of 280 kPa and 10°C, respectively, at the inlet to the nozzle. The nozzle throat area is 6.5 × 10-4 m2 and the ratio of the exit area to the throat area is 4. If the pressure on the exit plane of the nozzle is 170 kPa, find the Mach number and the temperature on the nozzle exit plane and the nozzle area at the point in the nozzle at which the normal shock wave occurs.

Reference no: EM131467075

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