Question: 5 . 1 6 Consider a rocket engine burning hydrogen and oxygen. The combustion chamber temperature and pressure are 4 0 0 0 K and

5.16 Consider a rocket engine burning hydrogen and oxygen. The combustion chamber temperature and pressure are 4000K and 15atm, respectively. The exit pressure is 1.174102atm. Calculate the Mach number at the exit. Assume that = constant =1.22 and that R=519.6J/kgK.

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