Q4: (14 Marks): A simple turbo jet engine developing a thrust of 25 kN and flying at a speed of 936 km/h. The engine consumes 0.0139 kg of fuel per each kilogram of air. The turbine inlet temperature is 1000 K. The polytropic efficiencies of the compressor and the turbine are the same and equal to 80%. The ambient conditions are 240 K and 40 kPa. Neglect all the other losses and take for air k-1.4, Cpa-1005 J/kg.K and for gas k-1.333, Cpg-1147 J/kg.K and R-287 J/kg.K for .both The stagnation temperature at the inlet of the compressor To1 = The stagnation pressure at the inlet of the compressor P01 = The stagnation temperature at the outlet of the compressor To2 = The pressure ratio of the compressor (Po2/Po1)is The stagnation pressure at the inlet of the turbine (Po3) is The stagnation temperature at the outlet of the turbine (To4) is The stagnation pressure at the outlet of the turbine (Po4) is The pressure at the nozzle exit is The gas velocity at the nozzle exit is The temperature at the nozzle exit is