Q1. A two-spool turbojet engine is operating at an altitude of h = 15,000 m at a Mach number of M = 1.85. The stagnation temperature entering the high-pressure turbine at the design point for the engine is T04 = 1800 K. a) Find T2, P2, To2, and Poz. b) At the design point- Poz = 26, and = 5. Find 023 P023 Poz c) Use this to find P023, P03, T023, and T03 at the design point. d) Then, determine the values of KLPS and KHPS. e) Next, find T045, T05, P045, and P0s at the design point. A4 f) Calculate and 445 A45 Ag g) Plot the spool pressure ratios for the high- and low-pressure compressors against the normalized mass flow rate per unit area for each high- and low-pressure compressors normalized by the normalized mass flow rate per unit area at the design point for their compressor. Assume that there is no pressure drop through the combustion chamber. Take ke = 1.3, ka = 1.4, Cpe = 1.244kJ/kgK, Cpe = 1.005kJ/kgK, Mpt = npc = 0.90. A4 Also, take 44 = 0.372 and = 0.464. A A23