A turbo-jet aircraft is flying with the velocity 800 km/h at 10700 m, where pressure and temperature are 0.24 bar and -50oC respectively. The compressor pressure ratio is 10/1 and maximum cycle temperature is 820oC. Calculate the thrust developed and the specific fuel consumption using the following information;
For Compressor & Diffuser – [CP = 1.005 kJ/kg and γ=1.4] – For air
For Combustion & Expansion – [CP = 1.15 kJ/kg and γ=1.333] – For product gases
Assume: Nozzle is converging nozzle
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