Aturbofan operates at 38,000 ft at mach 0.8. the compressor pressure ratio is 22.0 and the fan pressure ratio is 1.8. the fuel has a heating value of 17,900 btu/lbm and the exit total temperature from the burner is 2480°r. the core airflow is 155 lbm/sec and the bypass ratio is 5.50. the aerodynamic efficiencies of the compressor, fan, turbine, shaft, burner, primary nozzle and fan nozzle are 88%, 87%, 91%, 99.5, 92%, 95% and 95% respectively. the total pressure ratio (recovery factor) for the diffuser is 0.93. assume the total pressure ratio for the combustor is 0.97. the nozzles are both converging but might not be choked. find the developed thrust and tsfc. rerun this problem with a specific heat ratio of 1.4 and work the problem out by hand to compare with your code results.