A turbo jet aircraft is travelling at 925km/h in the atmospheric conditions of 0.45 bar and -26^oC. The compressor pressure ratio is 8/1. The air mass flow rate is 45 kg/sec and the maximum allowable cycle temperature is 800^oC. The compressor-turbine and jet pipe stagnation isentropic efficiencies are 85%, 89% and 90% respectively. The mechanical efficiency of the drive is 98% and combustion efficiency is 99%. Assuming the convergent nozzle for propulsion. A loss of stagnation pressure in the combustion chamber of 0.2 bar and a fuel of calorific value 43300 kJ/kg.

For product gases, (C_P = 1.15 kJ/kg. K  &   γ=1.333) & For air, (C_P =1.005 kJ/kg. K  &   γ=1.4)

Calculate;

(a) The required nozzle exit area 

(b) The thrust developed 

(c) The air fuel ratio

(d) The S.F.C