Explanation Write the expression for the Mach number at the exit of the nozzle. M 2 = { 2 k − 1 [ ( p o p 2 ) k − 1 / k − 1 ] } 1 / 2 (I) Here, the Mach number at exit is M 2 , the stagnation pressure is p o , the pressure at exit is p 2 and the specific heat ratio is k . Conclusion: The stagnation pressure is p o = 1 × 10 6 Pa and the critical pressure is p c = 528 kPa . Since, the back pressure is greater than the critical pressure. Hence the flow is subsonic throughout the nozzle and the exit pressure ( p 2 ) is equal to the back pressure ( p B ) . p 2 = p B = 843 kPa = 8.43 × 10 5 Pa Substitute 1

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Author: MORAN

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Chapter 9.14, Problem 39CU

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The Mach number at the exit for a back pressure of 843 kPa.

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Chapter 9.14, Problem 38CU

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The Mach number at the exit for a back pressure of 843 kPa .

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