P that (15 pts) Consider the fixed temperature ratio Brayton cycle and the pressure ratio optimizes (maximizes) the work output. Consider now that the compression process has two parts: i. isentropic free-stream compression by the inlet to approximately zero velocity P1.5 P1 =(1+1=1m) = (1 + V 1 M) / 1 P2 P1.5 ii. compression by the compressor Together, these two processes make up the total pressure rise due to compression: a. P2 P2 P1.5 = P1 P1.5 P1 P1.5 Plot the optimum compressor pressure ratio (12) as a function of flight Mach number, M, for different temperature ratios = 5,6,7). b. Write the equation for the Mach number that renders useless a compressor in an aircraft engine (M is a function of temperature ratio (3) T