Perform a cycle analysis of a turbojet operating at a cruise M = 0.85 at an altitude of 40,000 ft. The pressure ratio p03/p02 = 42 and the turbine inlet temperature T04 = 1800 K. Use a heating value LHV = 45,000 kJ/kg for the fuel. Use adiabatic efficiencies for components from the notes: d = 0.97, c = 0.85, t = 0.90, and n = 0.98. Let the burner efficiency b = 0.98 and assume a 2.0% pressure loss in the combustor (p04/p03 = 0.98). In the freestream and diffuser, cp = 1.0 kJ/kg-K. In the compressor use , = 1.03, in the combustor use , = 1.20, in the turbine use , = 1.23, from the turbine exit through the nozzle exit use , = 1.1. For , assume an ideal gas with MW = 29 g/mole. Use 1.0 kg/s of air as a basis for the calculation