An ideal ramjet engine is being designed for a mach 3.0 aircraft at an altitude of 33,000 ft. the fuel has a heating value of 18,600 btu/lbm and the burner exit total temperature is 3400°r. a thrust of 15,000 lbf is needed. what is the required airflow? what are the resulting nozzle exit and throat diameters? what is the resulting tsfc? for a fixed mach number, plot thrust and tsfc as a function of combustor exit temperature for ranges between the combustor inlet temperature and 4000°r.