3. ) A turbojet engine has a compressor pressure ratio of 30 and maximum temperature of 1700 K. The nozzle is to expand fully to the ambient pressure. For a flight Mach number of 0.85, Calculate: 1- Specific thrust 11. Thrust specific fuel consumption iii. Thermal efficiency IV. Propulsion efficiency V. Overall efficiency [0.965 kN-s/kg, 105.85 kg/k:N-hr, 0.538, 0.352, 0.1896] b) A front-mounted turbofan engine with a bypass ratio of 5 is to operate at the same core engine pressure ratio and maximum temperature as prescribed in the part (a) of the problem. The nozzle is to expand fully to the ambient pressure also. For fan pressure ratio of 1.5, calculate: 1. Specific thrust 1i. Thrust specific fuel consumption iii. Thermal efficiency IV. Propulsion efficiency V. Overall efficiency [1.266 kN-s/kg, 80.13 kg/kN-hr, 0.497, 0.503, 0.250] The ambient conditions and component efficiencies are given below. . Fuel heating value 45,000 k.J/kg. Gas constant R=287 J/kg-K. Components 7 Isentropic n Inlet 1.4 0.97 Compressor 1.4 0.85 Comb. chamber 1.3333 at exit 1 (combustion efficiency) Turbine 1.333 0.9 Fan 1.4 0.85 Jet nozzle 1.3333 0.98 Fan nozzle 1.4 0.97 Flight altitude Cruise Mach no. Ambient pressure, kPa |Ambient temperature, K 12.2 km 0.85 18.75 216.7