(a) Explanation Write the expression for the velocity for isentropic expansion at exit. V s = k R T s (I) Here, the velocity for the isentropic expansion at exit is V s , the specific heat ratio is k , the universal gas constant is R and the temperature for isentropic expansion at exit is T s . Write the expression for the velocity at nozzle exit. V e = η V s (II) Here, the velocity at the nozzle exit is V e and the isentropic efficiency is η . Write the expression for the pressure for isentropic expansion. p s p o = 1 [ 1 + ( k − 1 2 ) M 2 ] k k − 1 (III) Here, the stagnation pressure is p o , the pressure at the exit for the isentropic expansion is p s and the mach number is M . Conclusion: Substitute 1.4 for k and 1 for M in Equation (III). p s p o = 1 [ 1 + ( 1.4 − 1 2 ) ( 1 ) 2 ] 1.4 1.4 − 1 = 1 ( 1.2 ) 3.5 = 0.528 Refer to table 9.2 “Isentropic flow functions for an ideal gas with k = 1.4 ” to obtain the mach number and temperature ratio at isentropic pressure ratio p s p o = 0.528 as 1 and 0.8333 . Calculate the temperature ratio. T s T o = 0.8333 T s = ( 0 (b) To determine The temperature at the nozzle exit. (c) To determine The Mach number at the nozzle exit. (d) To determine The stagnation pressure in bar at nozzle exit. (e) To determine The mass flow rate at the exit of the nozzle.

8th Edition

ISBN: 9781119391630

Author: MORAN

Publisher: WILEY

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Chapter 9.14, Problem 131P

(a)

To determine

The velocity at the nozzle exit.

(b)

To determine

The temperature at the nozzle exit.

(c)

To determine

The Mach number at the nozzle exit.

(d)

To determine

The stagnation pressure in bar at nozzle exit.

(e)

To determine

The mass flow rate at the exit of the nozzle.

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Chapter 9.14, Problem 130P

Chapter 9.14, Problem 132P

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