Aerospace Engineering > GATE 2013 > Rocket Nozzle Performance
A rocket motor has a chamber pressure of 100 bar and chamber temperature of 3000 K. The ambient pressure is 1 bar. Assume that the specific heat at constant pressure is 1 kJ/kg-K Also assume that the flow in the nozzle is isentropic and optimally expanded. The exit static temperature in K is
Correct : a
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