In part (e) of Example 9.15 a convergingdiverging nozzle
Chapter 9, Problem 9.132(choose chapter or problem)
In part (e) of Example 9.15 a converging–diverging nozzle is considered that experiences a shock in the diverging section. At the nozzle exit for this case the pressure is \(53.3 \mathrm{lbf} / \mathrm{in} .^{2}\) Demonstrate that a converging nozzle also can achieve that exit pressure while flow is isentropic throughout from the same stagnation state as in part(e). Determine the Mach number at the exit of the converging nozzle.
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