A turbo jet engine is traveling at a speed of 236.11 m/sec under conditions 288K and 1.013 bar. The ram efficiency is 85%. Calculate the total pressure and total temperature of air after inlet diffuser. Take Cpa = 1.005, Y=1.4. For the above engine, the total temperature and total pressure at the inlet to the nozzle is 806k and 2.124 bar. The flow through nozzle is adiabatic with jet efficiency (total-to-static) 95%. Calculate the net specific thrust and thrust specific fuel consumption (TSFC) if fuel air ratio is 0.0122. take Cpg 1.16 and yg 1.33.