a 1. Consider the single-spool afterburning turbojet engine shown below, which is flying 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. Inlet Compressor Combustor 4 Turbine We will now zoom in on a single stage of the compressor. Using the station numbering in the figure to the right, Afterburner a) On one set of axes, plot profiles of the static and stagnation temperature versus station b) On another set of axes, plot profiles of the static and stagnation pressure versus station c) On one set of axes, plot profiles of the static and stagnation temperature through the stage d) On another set of axes, plot profiles of the static and stagnation pressure through the stage. [15 Marks] Inflow air direction (c) Rotor Nozzle A Blade direction (u) 2 Stator 3