A turbojet engine is designed for cruise conditions of 600mi/hr at an altitude of 10000 meters where the ambient temperature and pressure are -50 C and 26.5 kPa, respectively. The turbojet operates at a turbine inlet temperature (T3) of 867 C and a nozzle exit temperature (T5) of 412 C. The compressor pressure ratio is 7 and the compressor efficiency of 83%. Assuming the flow to be air only and using the air tables to obtain property values, find the exit velocity from the nozzle?