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The stagnation pressure and temperature of air supplied to a convergent/divergent nozzle are held constant at...

The stagnation pressure and temperature of air supplied to a convergent/divergent nozzle are held constant at values of 430K and 600kPa. The nozzle has an outlet area of 0.09m2 and an exit to throat area ratio of 2.51.

(i) Calculate the exit pressure required to produce a normal shock at the exit plane of the nozzle.

(ii) Calculate the mass flow rate of air through the nozzle when there is a normal shock at the exit plane.

(iii) Calculate the stagnation pressure immediately downstream of the normal shock described in part (i).

(iv) When a back pressure of 440kPa is applied to the exit of the converging/diverging nozzle described, calculate the Mach number at the exit plane.

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