4. A high bypass ratio turbofan is designed for a cruise condition of M 0.85, 11 000 m (pa = 0.2270 bar, Ta = 216.8 k, a = 295.2 m/s). The following data apply: Polytropic efficiencies of all components Intake efficiency Bypass ratio Fan pressure ratio Overall pressure ratio Turbine inlet temperature Mass flow rate Combustor loss 0.90 0.95 5.7 1.77 34 1350 K 220 kg/s 7% compressor delivery pressure Calculate the thrust developed and the specific fuel consumption. For calculations you can assume a simple two-spool configuration with separate nozzles.