Fundamentals of Aerodynamics
Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 9, Problem 9.10P

Consider the supersonic flow over an expansion corner, such as given in Figure 9.25. The deflection angle θ = 23 . 38 ° . If the flow upstream of the corner is given by M 1 = 2 , p 1 = 0.7 atm , T 1 = 630 ° R , calculate M 2 , p 2 , T 2 , ρ 2 , p 0 , and T 0 , 2 downstream of the corner. Also, obtain the angles the forward and rearward Mach lines make with respect to the upstream direction.

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