Engineering, 26.02.2020 01:45 Miguel1310
At the inlet to the ombustor of a supersonic ramjet(SCRAMjet), the flow Mach number is supersonic. For the fuel-air ratio(by mass) of 0.03 and a combustor exit temperature of 4800 degree R, calculate the inlet Mach number above which the flow will be unchoked. Assume one dimensional frictionless flow with lamda = 1.4, with the heat release per slug of fuel equal to 4.5x10^8 ft-lb. Also calculate change in entropy for the process
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At the inlet to the ombustor of a supersonic ramjet(SCRAMjet), the flow Mach number is supersonic. F...
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