Problem 15 At the inlet to the combustor of a supersonic combustion ramjet (SCRAMjet), the flow Mach number is supersonic. For a fuel-air ratio (by mass) of 0.03 and a combustor exit temperature of 4800°R, calculate the inlet Mach number above which the flow will be unchoked. Assume one-dimensional flow with k 1.4, with the heat release per slug of fuel equal to 4.5 x 108 ft-lb. frictionless