6. 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, $\gamma$, of 1.225. If the molecular mas of the combustion products is 21.79 kg/kmole, what is the theoretical characteristic exhaust velocity, C*, and the specific impulse, $I_{sp}$, for this new engine. (Problem 14-29 in Understanding Space)