Question 12.9: Shock Wave in a Converging–Diverging Nozzle If the air flowi...
Shock Wave in a Converging–Diverging Nozzle
If the air flowing through the converging–diverging nozzle of Example 12–7 experiences a normal shock wave at the nozzle exit plane (Fig. 12–35), determine the following after the shock: (a) the stagnation pressure, static pressure, static temperature, and static density; (b) the entropy change across the shock; (c) the exit velocity; and (d) the mass flow rate through the nozzle. Assume steady, one-dimensional, and isentropic flow with k = 1.4 from the nozzle inlet to the shock location.
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