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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
🗓 Dec 7, 2021
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Muskaan
🌐 India
Nice website
votes
Sabrina
🌐 India
Answer is fine but where is solution?
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