Explanation Given information: For steam of ideal gas is K=1.33 and R=461J/kg.K Find the exit Mach number: p p o = 70 k p a 100 k p a = ( 1 + 0.33 2 M a e 2 ) − 1.33 / 0.33 M a e x i t ≈ 0.75 We consider EES First we have to find h o = E N T H A L P Y ( s t e a m , p = 100 , T = 473 ) = 2875 k J / k g . K S o = E N T R O P Y ( s t e a m , p = 100 , T = 473 ) = 7.833 k J / k g . K Use energy equation at known pressure with exit: h o = 2875 = h e + V e 2 2 × 1000 h e = E N T H A L P Y ( s t e a m , p = 70 , s = 7.833 ) EES returns to the result h e = 2800 k j / k g V e = 385 m / s Exit temperature and the mass flow is T e = T E M P E R A T U R E ( s t e a m , p = 70 , s = 7 To determine Find the nozzle exit pressure and mass flow by using given data.

8th Edition

ISBN: 9780073398273

Author: Frank M. White

Publisher: McGraw-Hill Education

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Chapter 9, Problem 9.5CP

To determine

Find the mass flow rate and exit temperature by using given data.

To determine

Find the nozzle exit pressure and mass flow by using given data.

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Chapter 9, Problem 9.4CP

Chapter 9, Problem 9.6CP

Chapter 9 Solutions

Fluid Mechanics

Ch. 9 - Prob. 9.1P Ch. 9 - Prob. 9.2P Ch. 9 - If 8 kg of oxygen in a closed tank at 200°C and...Ch. 9 - P9.4 Consider steady adiabatic airflow in a duct....Ch. 9 - Prob. 9.5P Ch. 9 - Prob. 9.6P Ch. 9 - Prob. 9.7P Ch. 9 - Prob. 9.8P Ch. 9 - P9.9 Liquid hydrogen and oxygen are burned in a...Ch. 9 - P9.10 A certain aircraft flics at 609 mi/h at...

Ch. 9 - Prob. 9.11P Ch. 9 - Prob. 9.12P Ch. 9 - Consider steam at 500 K and 200 kPa. Estimate its...Ch. 9 - Prob. 9.14P Ch. 9 - Prob. 9.15P Ch. 9 - Prob. 9.16P Ch. 9 - Prob. 9.17P Ch. 9 - Prob. 9.18P Ch. 9 - Prob. 9.19P Ch. 9 - Prob. 9.20P Ch. 9 - P9.21 N?O expands isentropically through a duct...Ch. 9 - Given the pitot stagnation temperature and...Ch. 9 - Prob. 9.23P Ch. 9 - Prob. 9.24P Ch. 9 - Prob. 9.25P Ch. 9 - Prob. 9.26P Ch. 9 - P9.27 A pitot tube, mounted on an airplane flying...Ch. 9 - Prob. 9.28P Ch. 9 - Prob. 9.29P Ch. 9 - Prob. 9.30P Ch. 9 - Prob. 9.31P Ch. 9 - Prob. 9.32P Ch. 9 - Prob. 9.33P Ch. 9 - Prob. 9.34P Ch. 9 - Prob. 9.35P Ch. 9 - P9.36 An air tank of volume 1.5 m3 is initially at...Ch. 9 - Make an exact control volume analysis of the...Ch. 9 - Prob. 9.38P Ch. 9 - Prob. 9.39P Ch. 9 - Prob. 9.40P Ch. 9 - Prob. 9.41P Ch. 9 - Prob. 9.42P Ch. 9 - Prob. 9.43P Ch. 9 - Prob. 9.44P Ch. 9 - It is desired to have an isentropic airflow...Ch. 9 - Prob. 9.46P Ch. 9 - Prob. 9.47P Ch. 9 - Prob. 9.48P Ch. 9 - Prob. 9.49P Ch. 9 - Prob. 9.50P Ch. 9 - Prob. 9.51P Ch. 9 - Prob. 9.52P Ch. 9 - Prob. 9.53P Ch. 9 - Prob. 9.54P Ch. 9 - Prob. 9.55P Ch. 9 - Prob. 9.56P Ch. 9 - Prob. 9.57P Ch. 9 - Prob. 9.58P Ch. 9 - Prob. 9.59P Ch. 9 - Prob. 9.60P Ch. 9 - Prob. 9.61P Ch. 9 - Prob. 9.62P Ch. 9 - Prob. 9.63P Ch. 9 - Prob. 9.64P Ch. 9 - Prob. 9.65P Ch. 9 - Prob. 9.66P Ch. 9 - Prob. 9.67P Ch. 9 - Prob. 9.68P Ch. 9 - Prob. 9.69P Ch. 9 - Prob. 9.70P Ch. 9 - A converging-diverging nozzle has a throat area of...Ch. 9 - Prob. 9.72P Ch. 9 - Prob. 9.73P Ch. 9 - Prob. 9.74P Ch. 9 - Prob. 9.75P Ch. 9 - Prob. 9.76P Ch. 9 - P9.77 A perfect gas (not air) expands...Ch. 9 - Prob. 9.78P Ch. 9 - P9.79 A large tank, at 400 kPa and 450 K, supplies...Ch. 9 - Prob. 9.80P Ch. 9 - Prob. 9.81P Ch. 9 - Prob. 9.82P Ch. 9 - 1*9.83 When operating at design conditions (smooth...Ch. 9 - Prob. 9.84P Ch. 9 - A typical carbon dioxide tank for a paintball gun...Ch. 9 - Prob. 9.86P Ch. 9 - Prob. 9.87P Ch. 9 - Prob. 9.88P Ch. 9 - Prob. 9.89P Ch. 9 - Prob. 9.90P Ch. 9 - Prob. 9.91P Ch. 9 - Prob. 9.92P Ch. 9 - Prob. 9.93P Ch. 9 - Prob. 9.94P Ch. 9 - Prob. 9.95P Ch. 9 - Prob. 9.96P Ch. 9 - Prob. 9.97P Ch. 9 - Prob. 9.98P Ch. 9 - Prob. 9.99P Ch. 9 - Prob. 9.100P Ch. 9 - Prob. 9.101P Ch. 9 - Prob. 9.102P Ch. 9 - Prob. 9.103P Ch. 9 - Prob. 9.104P Ch. 9 - Prob. 9.105P Ch. 9 - Prob. 9.106P Ch. 9 - Prob. 9.107P Ch. 9 - Prob. 9.108P Ch. 9 - P9.109 A jet engine at 7000-m altitude takes in 45...Ch. 9 - Prob. 9.110P Ch. 9 - Prob. 9.111P Ch. 9 - Prob. 9.112P Ch. 9 - Prob. 9.113P Ch. 9 - Prob. 9.114P Ch. 9 - Prob. 9.115P Ch. 9 - Prob. 9.116P Ch. 9 - P9.117 A tiny scratch in the side of a supersonic...Ch. 9 - Prob. 9.118P Ch. 9 - Prob. 9.119P Ch. 9 - Prob. 9.120P Ch. 9 - Prob. 9.121P Ch. 9 - Prob. 9.122P Ch. 9 - Prob. 9.123P Ch. 9 - Prob. 9.124P Ch. 9 - Prob. 9.125P Ch. 9 - Prob. 9.126P Ch. 9 - Prob. 9.127P Ch. 9 - Prob. 9.128P Ch. 9 - Prob. 9.129P Ch. 9 - Prob. 9.130P Ch. 9 - Prob. 9.131P Ch. 9 - Prob. 9.132P Ch. 9 - Prob. 9.133P Ch. 9 - P9.134 When an oblique shock strikes a solid wall,...Ch. 9 - Prob. 9.135P Ch. 9 - Prob. 9.136P Ch. 9 - Prob. 9.137P Ch. 9 - Prob. 9.138P Ch. 9 - Prob. 9.139P Ch. 9 - Prob. 9.140P Ch. 9 - Prob. 9.141P Ch. 9 - Prob. 9.142P Ch. 9 - Prob. 9.143P Ch. 9 - Prob. 9.144P Ch. 9 - Prob. 9.145P Ch. 9 - Prob. 9.146P Ch. 9 - Prob. 9.147P Ch. 9 - Prob. 9.148P Ch. 9 - Prob. 9.149P Ch. 9 - Prob. 9.150P Ch. 9 - Prob. 9.151P Ch. 9 - Prob. 9.152P Ch. 9 - Prob. 9.153P Ch. 9 - Prob. 9.154P Ch. 9 - Prob. 9.155P Ch. 9 - Prob. 9.156P Ch. 9 - The Ackeret airfoil theory of Eq. (9.104) is meant...Ch. 9 - Prob. 9.1WP Ch. 9 - Prob. 9.2WP Ch. 9 - Prob. 9.3WP Ch. 9 - Prob. 9.4WP Ch. 9 - Prob. 9.5WP Ch. 9 - Prob. 9.6WP Ch. 9 - Prob. 9.7WP Ch. 9 - Prob. 9.8WP Ch. 9 - FE9.1 For steady isentropic flow, if the absolute...Ch. 9 - FE9.2 For steady isentropic flow, if the density...Ch. 9 - Prob. 9.3FEEP Ch. 9 - Prob. 9.4FEEP Ch. 9 - Prob. 9.5FEEP Ch. 9 - Prob. 9.6FEEP Ch. 9 - Prob. 9.7FEEP Ch. 9 - Prob. 9.8FEEP Ch. 9 - Prob. 9.9FEEP Ch. 9 - Prob. 9.10FEEP Ch. 9 - Prob. 9.1CP Ch. 9 - Prob. 9.2CP Ch. 9 - Prob. 9.3CP Ch. 9 - Prob. 9.4CP Ch. 9 - Prob. 9.5CP Ch. 9 - Prob. 9.6CP Ch. 9 - Professor Gordon Holloway and his student, Jason...Ch. 9 - Prob. 9.8CP Ch. 9 - Prob. 9.1DP Ch. 9 - Prob. 9.2DP

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