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Q: Air enters a normal shock at 22.6 kPa, 217 K, and 680 m/s. Calculate the stagnation pressure and Mach number upstream of the shock, as well as pressure, temperature, velocity, Mach number, and stagnation pressure downstream of the shock. You must include all the units which are needed to solve the given problem.Your steps and calculation should be clear and understanadable.