Explanation Write the expression for the pressure ratio for nozzle exit. p o p * = [ 1 + ( k − 1 2 ) M 2 ] k k − 1 (I) Here, the stagnation pressure is p o , the pressure at the exit for the isentropic expansion is p * and the mach number is M . Write the expression for the Mach number at the exit of the nozzle. M = [ ( 2 k − 1 ) ( p o p ) k − 1 k − 1 ] 1 2 (II) Here, the pressure at exit of the nozzle is p , the specific heat ratio is k , Conclusion: Here, the converging nozzle can achieve the pressure 53.3 lbf / in 2 at its exit only if p * ≤ 53.3 lbf / in 2 . Substitute 100 lbf / in 2 for p o , 1.4 for k and 1 for M in Equation (I). p * = ( 100 lbf / in 2 ) [ 1 + ( 1.4 − 1 2 ) ( 1 ) 2 ] 1.4 1.4 − 1 = ( 100 lbf / in 2 ) ( 1

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Chapter 9.14, Problem 132P

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Whether a converging nozzle can achieve the same exit pressure when the flow is isentropic at stagnation state.

The Mach number at the exit of the nozzle.

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Chapter 9.14, Problem 131P

Chapter 9.14, Problem 133P

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Whether a converging nozzle can achieve the same exit pressure when the flow is isentropic at stagnation state. The Mach number at the exit of the nozzle.

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Whether a converging nozzle can achieve the same exit pressure when the flow is isentropic at stagnation state.

The Mach number at the exit of the nozzle.