Assume an aircraft with a high bypass ratio engine is flying at 230 m/s with local far-field static pressure and temperatures of 25 kPa and 220 K. The core of the engine takes in 25 kg/s of air and the engine bypass ratio is 8. If the pressure ratio of the fan is 1.5 determine the thrust of the bypass jet. You can assume the fan efficiency is 89% and the nozzle efficiency is 100.