A jet engine propels an aircraft at 300 m/s through air at 60 kPa and 0 C. The inlet diameter of this engine is 2 m, the compressor pressure ratio is 10, and the temperature at the turbine inlet is 450C. Determine the velocity at the exit of this engine's nozzle and the thrust produced. Assume ideal operation for all components and constant properties at room temperature and neglect the diffuser effect.