Example 10.1A uniform supersonic airflow traveling at Mach 2.0 passes over a wedgeM2(Fig. 10E.1). An oblique shock, making an angle of 40° with the flow P= 20 kPaT=-10 °C0=40%direction, is attached to the wedge under these flow conditions. If the staticM 2.0pressure and temperature in the uniform flow are, respectively, 20 kPa and-10 °C, determine the static pressure and temperature behind the wave, theMach number of the flow passing over the wedge, and the wedge half-angle. Figure 10E.1:

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Example 10.1 A uniform supersonic airflow traveling at Mach 2.0 passes over a wedge M2 (Fig. 10E.1). An oblique shock, making an angle of 40° with the flow Pi 20 kPa direction, is attached to the wedge under these flow conditions. If the static T =-10 °C 0 40% M-2.0 pressure and temperature in the uniform flow are, respectively, 20 kPa and -10 °C, determine the static pressure and temperature behind the wave, the Mach number of the flow passing over the wedge, and the wedge half-angle. Figure 10E.1:

Example 10.1 A uniform supersonic airflow traveling at Mach 2.0 passes over a wedge M2 (Fig. 10E.1). An oblique shock, making an angle of 40° with the flow Pi 20 kPa direction, is attached to the wedge under these flow conditions. If the static T =-10 °C 0 40% M-2.0 pressure and temperature in the uniform flow are, respectively, 20 kPa and -10 °C, determine the static pressure and temperature behind the wave, the Mach number of the flow passing over the wedge, and the wedge half-angle. Figure 10E.1:

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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