3. Compare the thrust (Tramjet/Tturbojet) and thrust specific fuel consumption (TSFCramjet/TSFC turbojet) of a turbojet and a ramjet which are being compared for a Mach number of Ma 1.8 and an altitude 17,000 m, where the ambient temperature and pressure are -56 C and 8.79 kPa, respectively. The turbojet compressor pressure ratio is 6, and the maximum allowable temperature is 1173 K. For the ramjet, the maximum temperature is 2300 K. Both engines are the same size, and for simplicity ignore aerodynamic and mechanical losses in both engines. Conventional hydrocarbon fuels are to be used with a heating value of 43 MJ/kg. Assume the exhaust is perfectly expanded for both engines. Assume y 1.4 and Cp = 1.005 kJ/(kg.K). [50 Marks]