2. 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 BTUlem and the burner exit total temperature is 3400R. A thrust of 15,000 lbf is needed. What is the required airow? What are the resulting nozzle exit and throat diameters? What is the resulting TSFC? For a xed Mach number, plot thrust and TSFC as a function of combustor exit temperature for ranges between the combustor inlet temperature and 4000R