An ideal bypass turbojet (no losses in compressor, burner, turbine, nozzle, fan, and fan nozzle) has a bypass ratio 'lj! , of 8: 1 and a maximum turbine inlet temperature of 1200 k. at takeoff the ambient conditions are 298 k and 101 kpa. the bypass nozzle exhaust and core engine nozzle exhaust velocities are identical. what compressor pressure ratio will maximize takeoff thrust? for ease of calculation the approximation f < < 1 may be used (f being the fuel-air ratio for the core engine) and the specific heat ratio 'y may be taken to be 1.4 throughout.