A rocket engine is powered by liquid hydrogen and oxygen. THe combustion gas is accelerated to supersonic speed through a convergent divergent nozzle. It is designed to produce an exhaust gas velocity of 3500m/s. the gas temperature and pressure are 1500K and 40200Pa respectively at the nozzle exit. Assume γ = 1.2 and R = 692.8J/kg.K for the hydrogen and oxygen combustion gas mixture


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  • $\begingroup$ Have you worked, I mean yourself, on this exercise ? $\endgroup$ – Jean Marie Jan 11 at 16:27
  • $\begingroup$ Yes i have but my answer is wrong. $\endgroup$ – anabong Jan 11 at 16:34
  • $\begingroup$ Then show what you have attempted. It will help people to spot where you take a bad path... Besides, this question should be asked in a physics forum. $\endgroup$ – Jean Marie Jan 11 at 16:39
  • $\begingroup$ thank you for the advise. $\endgroup$ – anabong Jan 11 at 16:42
  • $\begingroup$ I used stagnation temperature formula. To/T = 1 + [(gamma -1)/2][Mach^2] to find the stagnation temperature. $\endgroup$ – anabong Jan 11 at 16:45