A turbojet engine operates on an airplane that flies at altitude H = 8000 m. The compressor pressure ratio is \pi C = 9, and the efficiency of the compressor is 85%. Air enters the compressor at a rate of 50 kg/s. The pressure drop in the combustor is 4%, and the combustor efficiency is 96%. The turbine entry temperature is 1400 K, and the turbine efficiency is 89%. The nozzle exit gas pressure is 1% above the compressor inlet pressure. Compute the compressor work, turbine work, thermal efficiency and net power of the turbojet engine. Use thermodynamic tables for all calculations