Consider an ideal turbojet engine with afterburner operating at the below conditions and, using excel sheet or MATLAB, generate the below performance curves of specific thrust, specific fuel consumption, fuel to air ratio, and efficiencies as function of the flight Mach number Mo and the compressor pressure ratio c. T = 390 R, y = 1.4, c, = 0.24 Btu/(lbm.R), hp = 18400 Btu/lbm, T4 = 3000 R, and T = 4000 F/m,[lbf/(lbm/s)] S 3 SAB 160 140 120 100 80 60 40 20 0 0 0.000 0.035 0.030 0.025 0,000- 0.150- 0.010 0.005 Fl- 0.000 1 5 10 S max Fl 15 20 -AN--- % 3.0 30 M-0 0.5 1.0 1.5 Mo=3 2.0 25 2.5 16 61 20 15 1.0 0.5 M-0 35 20 1.8 16 1.4 1.2 1.0 40 S[(lbm/hr)/lbf)