Uniform air flow at Mach 3 passes into a concave corner of angle 15°, as shown in Figure P6.1. The pressure and temperature in the supersonic flow are, respectively. 72 kPa and 290 K. Determine the tangential and normal components of velocity and Mach number upstream and downstream of the wave. Also, find the static and stagnation pressure ratios across the wave. How great would the corner angle have to be before the shock would detach from the corner? 15°

Uniform air flow at Mach 3 passes into a concave corner of angle 15°, as shown in Figure P6.1. The pressure and temperature in the supersonic flow are, respectively. 72 kPa and 290 K. Determine the tangential and normal components of velocity and Mach number upstream and downstream of the wave. Also, find the static and stagnation pressure ratios across the wave. How great would the corner angle have to be before the shock would detach from the corner? 15°

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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