= A Turbojet engine at SLS conditions (Po 101 kpa, To: 288 K). If the Engine pressure ratio EPR = Pts/Pt2 = 3.14 and the Specific thrust ST= 700 m/s. At design condition calculate the following: a. Compressor pressure ratio TLC b. Turbine inlet temperature Tt4, c. The type of nozzle and its condition for maximum thrust. Assume the following: The compressor and turbine polyropic efficiencies ec = et = 0.9. = M 1 Intake pressure loss (a = Tamax nr), Nr = (1-0.075 (M. - 1)1.35,1 < < < - Intake, Burner and nozzle pressure loss (dmax, b, AB, n = 0.97), b = 0.97 Specific heat ratio for compressor and turbine c = 1.4, Yt = 1.33 C = YR The fuel heating value hPR = 47 MJ/kgf, Nm (1+f) = 1 Y-1