2. Consider the single-spool afterburning turbojet engine shown below, which is flying at a subsonic Mach number. This is a non-ideal system with appropriate losses and non-negligible flow velocity throughout. Both the combustor and afterburner can be treated as constant area ducts. [18 Marks] Compressor Inlet 2, Combustor Turbine Afterburner Nozzle a) On one set of axes, plot profiles of the static and stagnation temperature versus station (along the engine). Temperature a Pressure 1 2 @= 3 14 ST 5 15 16 .**. b) On another set of axes, plot profiles of the static and stagnation pressure versus station (along the engine). 5 6 T To ****** P Po a 1 2 3 4 6 Note: Sketch similar plots on your solution papers. No vertical grid lines are necessary and 10 horizontal grid lines are adequate. Also note that this is a qualitative question - no numbers should be used for temperature and pressure.