Unsure on the Calculation The answer is: Isp initial = 383.9s a0 = 1263 m/s C* = 1747 m/s Thermochemical analys

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Unsure on the Calculation
The answer is: Isp initial = 383.9s a0 = 1263
m/s C* = 1747 m/s
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, Y, of 1.225. If the molecular mass of the
combustion products is 21.79 kg/kmole, what is the theoretical
characteristic exhaust velocity, C*, and the specific impulse, Isp,
for this new engine.