solve it and write all steps

Part(2b): Apply the steps for parametric cycle analysis for engine in part (2a) working at the same above the above-mentioned ideal mixed-now turbofan listed performance parameters, when the afterburnelated fuel to air ratio to determine the below ratio of 25 , a bypass ratio of 0.5 , and flight Mach of is off. The engine has a compressor pressure R). Assume =1.4,cp=0.24Btu(Ibm. R), and hpR=1.6 at an altitude of 40kft-altitude (T0=389.97 a) Maximum cycle temperature in R, b) Specific thrust in Ibf(Ibm/s), c) Thrust specific fuel consumption in (Ibm/s)/bbf, and d) Thermal, propulsive, and overall efficiencies of the engine