Q2) Uniform airflow at Mach 3 passes into a concave corner of angle 15°, as shown in Figure. The pressure and temperature in the supersonic flow are, respectively, 72 kPa and 290K. Determine the tangential and normal components of velocity and Mach number upstream and downstream of the wave for the weak shock solution. Also find the static and stagnation pressure ratios across the wave. M1 = 3

Q2) Uniform airflow at Mach 3 passes into a concave corner of angle 15°, as shown in Figure. The pressure and temperature in the supersonic flow are, respectively, 72 kPa and 290K. Determine the tangential and normal components of velocity and Mach number upstream and downstream of the wave for the weak shock solution. Also find the static and stagnation pressure ratios across the wave. M1 = 3

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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