pressure 10-stage compressor with a pressure ratio of 24:1 (This does not include the fan, just the compressor. Air compressed through fan first 2.2:1, then more compression through compressor 24:1) Two-stage high pressure turbine powering the compressor Four-stage low pressure turbine powering the fan (note separate turbines for compressor and fan) Ceramic matrix composite materials enable a burner temperature of 1550 K using A-1 kerosene "Jet A-1" fuel that has a heating value of 42.8 MJ/kg 6.5:1 bypass ratio Cruise is Mach 0.9 at 51,000 ft. where the pressure is 11 kPa and temperature is 216 K Separate exhaust streams with converging nozzles a) Calculate the core exhaust velocity. b) Calculate the bypass exhaust velocity. c) Calculate the specific thrust (thrust per unit core mass flow rate). d) Calculate the TSFC e) If the fan diameter is 132 cm, estimate the thrust