A turbojet engine with a convergent divergent nozzle expands the flow such that=0.8. The engine has the following data at flying Mach number 2 Tc 10, T41400 K, ecet = 0.9.Ye = 1.4, Cpc = 1.005- kJ kgK Symbol Tamax Q nm 7b Yt = 1.34, Cpt = 1.135- TEN R kJ kgk Value 0.95 42800000 J/(kg fuel) 0.99 0.99 0.98 0.97 Combustion chamber pressure ratio Nozzle pressure ratio Air Gas constant 287 J/(kg.K) If the jet velocity is 1025 m/sec, determine the thermal efficiency and the flight altitude in meters. Description Diffuser pressure ratio Fuel heating value Mechanical efficiency Combustion efficiency