Answered: M1 = 10 P = 1 atm Compression wave 0 =…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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Question

Consider the supersonic flow over a flat plate at an angle of attack, as
sketched . As stated , the flow direction downstream of the trailing edge of the plate, behind the trailing edge shock and expansion waves, is not precisely in the freestream direction.
Why? Outline a method to calculate the strengths of the trailing edge
shock and expansion waves, and the direction of the flow downstream of
the trailing edge.

M1 = 10
P = 1 atm
Compression wave
0 = 15°
(a) Isentropic compression corner
M1 = 10
Pi = 1 atm
Shock wave
0= 15°
(b) Shock compression corner
Figure 9.35 Figures for (a) Example 9.9 and (b) Example 9.10.

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