mahayess5267 mahayess5267

21-11-2022
Physics

contestada

air at a stagnation pressure of 700 kpa flows isentropically through a converging-diverging nozzle. the (supersonic) design pressure at the nozzle exit is 56 kpa. if the back pressure is raised gradually, thereby creating a shock in the divergent portion of the nozzle, calculate:

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