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Thermochemical analysis for a new rocket engine design using LOX and RP-1 predicts the combustion temperature...

Thermochemical analysis for a new rocket engine design using LOX and RP-1 predicts the combustion temperature will be 3415 K with a ratio of specific heats of 1.225. If the molecular mass of the combustion products is 21.79 kg/kmol, what is the theoretical characteristic exhaust velocity, and specific impulse for this new engine?

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