Determine the specific thrust and specific fuel consumption for a simple turbojet engine, which has the following component performance at the design point at which the cruising speed Ca and altitude are 270 m/s and 5000 m respectively. (525 N.s/kg, 0.122 kg/N.h) inlet- Compressor pressure ratio Turbine inlet temperature Isentropic efficiency: Yair Ygas Cp air Cp gas R low-pressure compressor www. of compressor, nc of turbine, n of intake, ni of propelling nozzle, nj high-pressure high-pressure compressor turbine turbojet THE IIIE GALLE burner low-pressure turbine 8.0 (total to total) 1200 K 87% 90% 93% nozzle 95% 99% Mechanical transmission efficiency, m Combustion efficiency, nb Combustion pressure loss, 4pb pressure From the I.S.A table at 5000 m, pa=0.5405 bar and T=255.7 K Take: Fuel calorific value 98% 4% of compressor delivery 43 MJ/kg 1.4 1.333 1005 J/kg.K 1148 J/kg.K 287 J/kg.K