A turbo-jet aircraft is flying with the velocity 800 km/h at 10700 m, where pressure and temperature are 0.24 bar and -50^oC respectively. The compressor pressure ratio is 10/1 and maximum cycle temperature is 820^oC. Calculate the thrust developed and the specific fuel consumption using the following information;

ɳ_entery-duct = 90%  ɳ_c = 90%  ɳ_combustion = 98%   ɳ_T = 92%   ɳ_m = 98%       ɳ_N = 92%

Stagnation pressure loss in the combustion chamber = 0.14 bar

Cv_fuel = 43300 kJ/kg   A₂ = 0.08 m2

For Compressor & Diffuser – [C_P = 1.005 kJ/kg   and   γ=1.4] – For air

 For Combustion & Expansion – [C_P = 1.15 kJ/kg   and   γ=1.333] – For product gases

Assume: Nozzle is converging nozzle