Fox And Mcdonald's Introduction To Fluid Mechanics

9th Edition

ISBN: 9781118921876

Author: Pritchard, Philip J.; Leylegian, John C.; Bhaskaran, Rajesh

Publisher: WILEY

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Textbook Question

Chapter 12, Problem 84P

A normal shock wave exists in an airflow. The absolute pressure, velocity, and temperature just upstream from the wave are 207 kPa, 610 m/s, and −17.8°C, respectively. Calculate the pressure, velocity, temperature, and sonic velocity just downstream from the shock wave.

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Chapter 12, Problem 83P

Chapter 12, Problem 85P

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In compressible flow, velocity measurements with a Pitot probe can be grossly in error if relations developed for incompressible flow are used. Therefore, it is essential that compressible flow relations be used when evaluating flow velocity from Pitot probe measurements. Consider supersonic flow of air through a channel. A probe inserted into the flow causes a shock wave to occur upstream of the probe, and it measures the stagnation pressure and temperature to be 620 kPa and 340 K, respectively. If the static pressure upstream is 110 kPa, determine the flow velocity.

Consider a normal shock wave in a supersonic airstream where the pressure upstream of the shock is 1 atm. Calculate the loss of total pressure across the shock wave when the upstream Mach number is (a) M1 = 2.5, and (b) M1 = 4.5. Compare these two results and comment on their implication

The pressure ratio across a normal shock wave in air is 4.5. What are the Mach numbers in front of and behind the wave? What are the density and temperature ratios across the wave?

Chapter 12 Solutions

Fox And Mcdonald's Introduction To Fluid Mechanics

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