The jet is flying at M = 1.3, where the absolute air pressure is 50 kPa. If a shock forms at the inlet of the engine, determine the Mach number of the air just within the engine where the diameter is...

The jet is flying at M = 1.3, where the absolute air pressure is 50 kPa. If a shock forms at the inlet of the engine, determine the Mach number of the air just within the engine where the diameter is 0.6 m. Also, what is the pressure and the stagnation pressure in this region? Assume isentropic flow within the engine.