Fox and McDonald's Introduction to Fluid Mechanics

9th Edition

ISBN: 9781118912652

Author: Philip J. Pritchard, John W. Mitchell

Publisher: WILEY

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Textbook Question

Chapter 12, Problem 89P

The stagnation temperature in an airflow is 149°C upstream and downstream from a normal shock wave. The absolute stagnation pressure downstream from the shock wave is 229.5 kPa. Through the wave the absolute pressure rises from 103.4 to 138 kPa. Determine the velocities upstream and downstream from the wave.

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Chapter 12, Problem 88P

Chapter 12, Problem 90P

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Chapter 12 Solutions

Fox and McDonald's Introduction to Fluid Mechanics

Ch. 12 - Air is expanded in a steady flow process through a...Ch. 12 - Five kilograms of air is cooled in a closed tank...Ch. 12 - Air is contained in a piston-cylinder device. The...Ch. 12 - Calculate the power delivered by the turbine per...Ch. 12 - If hydrogen flows as a perfect gas without...Ch. 12 - A 1-m3 tank contains air at 0.1 MPa absolute and...Ch. 12 - Air enters a turbine in steady flow at 0.5 kg/s...Ch. 12 - Natural gas, with the thermodynamic properties of...Ch. 12 - Carbon dioxide flows at a speed of 10 m/s in a...Ch. 12 - In an isothermal process, 0.1 cubic feet of...

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