Find shock waves in the nozzle

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Reference no: EM131467094

Question: A convergent-divergent nozzle is designed to expand air from a chamber in which the pressure is 700 kPa and the temperature is 35°C to give Mach 1.6. The mass flow rate through the nozzle under design conditions is 0.012 kg/s. Find

a. The throat and exit areas of the nozzle

b. The design back-pressure and the temperature of the air leaving the nozzle with this back-pressure

c. The lowest back-pressure for which there will be no supersonic flow in the nozzle

d. The back-pressure below which there are no shock waves in the nozzle.

Reference no: EM131467094

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