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.