Calculate the temperature and density of the flow at the exit. Assume that the flow is isentropic and (of course) compressible.

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A supersonic nozzle is also a convergent- divergent duct, which is fed by a large reservoir at the inlet to the nozzle. In the reservoir of the nozzle, the pressure and temperature are 10 and 300 K, respectively. At the nozzle exit, the pressure is 1 atm. Calculate the temperature and density of the flow at the exit. Assume that the flow is isentropic and (of course) compressible.

 

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