Explanation Given: Specific heat ratio, k = 1.4 Gas constant, R = 287 J / k g . K Temperature at section 1, T 1 = 432 K Temperature in tank, T 0 = 500 K Mach number at section 1, M a 1 = 0.89 Pressure at section 1, P 1 = 120 k P a Pressure in the tank, P 0 = 200 k P a Area at section 1, A 1 = 0.15 m 2 First of all, Velocity at section 1, V 1 = M a 1 k R T V 1 = 0.89 1.4 × 287 × 432 V 1 = 0.8 173577.6 V 1 = 370

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ISBN: 9781308529622

Author: White

Publisher: MCG/CREATE

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Chapter 9, Problem 9.5FEEP

To determine

Mass flow rate when area at section 1 is given.

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Chapter 9, Problem 9.4FEEP

Chapter 9, Problem 9.6FEEP

Chapter 9 Solutions

FLUID MECHANICS >C<

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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