Calculate the variation with Tt4 of exit Mach number, exitvelocity, specific thrust. Fuel/air ratio, and thrust specific fuelconsumption of an ideal turbojet engine for compressor pressureratios of 10 and 20 at a flight Mach number of 2 and T0=217K.Perform calculations at Tt4 values of 2400K, 2200K, 2000K and1800K. Use hPR= 42,800kJ/kg, cp= 1.004kJ/kg and γ= 1.4.
