Consider an ideal turbojet at flight conditions: To =220 K, PO = 20 kPa, and Mo= 0.8. Calculate and plot: 1) the specific thrust, 2) f, and 3) ISP versus the compressor stagnation pressure ratio (πc). Perform calculations for Tt, A=1600 K and 1800 K and for πc from 1 to 50. The fuel heat of combustion is hf= 42,800 kJ/kg. What πc maximizes thrust at the two peak stagnation temperatures?