2. A double-spool turbofan engine is used to power an aircraft flying at speed of 250 m/s at an altitude of 11,000 m, where ambient temperature is -50C and pressure is 22.7 kPa. As shown below, the low-pressure turbine drives the fan and low-pressure compressor, while the high- pressure turbine drives the high-pressure compressor. Inlet and outlet temperature and velocity of engine are plotted beside the engine layout. The engine has the following data: Bypass ratio P = 8. Total ingested air flow rate ma = 180 kg/s. Overall pressure ratio Pos/Poa = 35. Pressure ratio of high-pressure compressor is four times that of the low-pressure compressor; HPC = 4LPC. Fuel heating value QR = 43 MJ/kg. (10 250 m/s T -50C 306m/s -40C Core stream 543.2 m/s 306m/s -40C 250 m/s -50C 592C Assuming all processes are ideal. Also assume the flow capture area is the same as the engine inlet area and the bypass and core nozzle areas are the same as the respective capture areas. Find, a) Whether the nozzles are choked or not b) Pressure ratios f, LPC, and C c) Turbine inlet temperature T06 and fuel to air ratio f d) The thrust force e) TSFC [unit in mg/(N s)] [30 Marks]