1. A uniform supersonic air flow at Mach 2.0 passes over a wedge. An oblique shock, making an angle of 40° with the flow direction, is attached to the wedge. If the static pressure and temperature in the freestream are 0.5 x 10° N/m? and 0°C, determine the static and temperature behind the wave, the Mach number of the flow passing over the wedge, and the wedge angle. pressure

1. A uniform supersonic air flow at Mach 2.0 passes over a wedge. An oblique shock, making an angle of 40° with the flow direction, is attached to the wedge. If the static pressure and temperature in the freestream are 0.5 x 10° N/m? and 0°C, determine the static and temperature behind the wave, the Mach number of the flow passing over the wedge, and the wedge angle. pressure

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

1. A uniform supersonic air flow at Mach 2.0 passes over a wedge. An
oblique shock, making an angle of 40° with the flow direction, is
attached to the wedge. If the static pressure and temperature in the
freestream are 0.5 x 10 N/m2 and 0°C, determine the static pressure
and temperature behind the wave, the Mach number of the flow passing
over the wedge, and the wedge angle.

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