The answer should start from oblique, oblique and then normal shock waves.

The propulsion system is a jet engine with an inlet as shown in figure 1 and characterised by the parameters found in Table 1. The flow between the downstream side of the normal shock and the compressor face is isentropic; the ratio of the duct area at the compressor face to that at the normal shock (which may be considered to be the narrowest point of the stream tube) is 1.75. The area of the catchment tube that supplies the engine (not including the excess flow diverted into the dump slot on top of the intake) is known to be 1.25m2 at a position far upstream of the intake itself. Table 1: Engine Data Find the stagnation temperature and pressure of the flow at the compressor face after it has passed through the system of shocks shown in figure 3, ie., an oblique shock with a flow deflection of 8 degrees, followed by another oblique shock with a flow deflection of 5 degrees, followed by a normal shock