You are tasked with the preliminary design of a jet engine. You would like to obtain a thrust of 100kN with as high of a propulsive efficiency as possible. Your turbine inlet temperature cannot exceed 1300C. Assume the plane is flying at 300 m/s at an altitude of 5 km. Your company has access to two different compressors: Compressor A B Pressure Ratio 12.2 5.1 Isentropic Efficiency 81% 90% The only turbine available has an isentropic efficiency of 90%. Assume there are no losses to friction in the nozzle or diffuser. a) Which compressor should you use? b) What is the mass flow of air necessary to generate the required thrust?