Calculate the variation with T4 of exit Mach number, exit velocity, specific thrust, fuel/air ratio, and thrust specific fuel consumption of an ideal turbojet engine for compressor pressure ratios of 10 and 20 at a flight Mach number of 2 and To = 217 K. Perform calculations at T4 values of 2400, 2200, 2000, and 1800 K. Use hpR = 42,800 kJ/kg, Cp = 1.004 kJ/(kg-K), and y = 1.4. DO NOT compare results with the output of the PARA computer program.