An aircraft gas turbine engine operating on a Brayton cycle has a cold ASC thermal efficiency of 25.0% when the intake air is at 20.0°C and the combustion chamber outlet temperature is at 1200.°C. Assuming k = 1.40, determine
a. The isentropic pressure ratio of the engine.
b. The isentropic compression ratio of the engine.
c. The isentropic outlet temperature of the engine's compressor.
d. The optimum isentropic pressure ratio for maximum isentropic power output from the engine.
e. The optimum isentropic compression ratio for maximum isentropic power output from the engine.
f. The engine's thermal efficiency when operated at the maximum isentropic power output.