(a) Explanation Write the expression for the critical pressure ratio. p 2 * p 0 = ( 2 k + 1 ) k k − 1 (I) Here, the stagnation pressure is p 0 , the adiabatic index is k . Write the expression for the temperature ratio. T 2 T 0 = 2 k + 1 (II) Here, the stagnation temperature is T 0 . Write the expression for the exit velocity of the gas. V 2 = 2 g ( h 0 − h 2 ) (III) Here, the acceleration due to gravity is g , the stagnation enthalpy is h 0 and at exit is h 2 . Write the expression for the mass flow rate. m ˙ = A 2 V 2 p 2 R T 2 (IV) Here, the exit area of the nozzle is A 2 . Conclusion: Substitute 1.4 for k , 120 lbf / in 2 for p 0 in Equation (I). p 2 * 120 lbf / in 2 = ( 2 1.4 + 1 ) 1.4 1.4 − 1 p 2 * = 120 lbf / in 2 × 0.528 p 2 * = 63.36 lbf / in 2 Since p 2 * is 63.36 lbf / in and given discharger condition is 60 lbf / in 2 . So the nozzle is chocked. Substitute 1.4 for k and 600 ° R for T 0 I Equation (II). T 2 600 ° R = 2 2.4 T 2 = 600 ° R × 0.8333 T 2 = 500 ° R Substitute 143 (b) To determine The mass flow rate for C O 2 . (c) To determine The mass flow rate for argon gas.

Fundamentals of Engineering Thermodynamics

8th Edition

ISBN: 9781118832318

Author: MORAN

Publisher: WILEY

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Chapter 9.14, Problem 124P

(a)

To determine

The mass flow rate for air.

(b)

To determine

The mass flow rate for CO2.

(c)

To determine

The mass flow rate for argon gas.

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Chapter 9.14, Problem 123P

Chapter 9.14, Problem 125P

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Fundamentals of Engineering Thermodynamics

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