Design a turbojet engine to flight at an altitude of 10000m. The pressure ratio across the compressor is 3. The turbojet inlet temperature is 1400k. The propulsion thrust must be around 32000N and the Mach number 0.8. Design based on your best knowledge the following components of the engine: a) Diffuser ans Nozzles. b) Compressor and Turbine. Determine the following parameters. a) The pressure and temperatures at each principal state in kPa and k. b) Air mass flow rate. c) The velocity at the nozzle exit. d) Power of the turbo-components. e) Fuel flow rate necessary to power the engine. f) Performance parameters (SFC, TSFC, etc.) Detail and combine your procedure, assumptions, and conservation laws with the best design practices of the turbomachine.