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 42P
Air passes through a normal shock in a supersonic wind tunnel. Upstream conditions are M1 = 1.8, T'1 =270K, and p1 = 10.0 kPa absolute. Downstream conditions are M2 = 0.6165, T2 = 413.6 K. and p2 = 36.13 kPa absolute. (Four significant figures are given to minimize round off errors.) Evaluate local isentropic stagnation conditions (a) upstream from, and (b) downstream from, the normal shock. Calculate the change in specific entropy across the shock. Plot static and stagnation state points on a Ts diagram.
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Chapter 12 Solutions
Fox And Mcdonald's Introduction To Fluid Mechanics
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