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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Chapter 12, Problem 36P
A supersonic wind tunnel test section is designed to have M = 2.5 at 15°C and 35 kPa absolute. The fluid is air. Determine the required inlet stagnation conditions, T0 and p0. Calculate the required mass flow rate for a test section area of 0.175 m2.
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Chapter 12 Solutions
Fox And Mcdonald's Introduction To Fluid Mechanics
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