Q.1. A uniform supersonic air flow travelling at a Mach number of 2.5 passes over a wedge which deflects the flow by 15", as shown in the figure. If the pressure and temperature in the uniform flow are 40 kPa and 263 K, respectively, determine the shock wave angle, Mach number, pressure and temperature downstream of the oblique shock wave. Oblique Sheck Wave M=15 T= 263 K 15

Elements Of Electromagnetics
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Q.1. A uniform supersonic air flow travelling at a Mach number of 2.5 passes over
A wedge which deflects the flow by 15", as shown in the figure. If the pressure and
temperature in the uniform flow are 40 kPa and 263 K, respectively, determine the
shock wave angle, Mach number, pressure and temperature downstream of the
oblique shock wave.
Oblique
Sheck Waye
M= 1.5
T=263 K
15
F- 40 KPa
Transcribed Image Text:Q.1. A uniform supersonic air flow travelling at a Mach number of 2.5 passes over A wedge which deflects the flow by 15", as shown in the figure. If the pressure and temperature in the uniform flow are 40 kPa and 263 K, respectively, determine the shock wave angle, Mach number, pressure and temperature downstream of the oblique shock wave. Oblique Sheck Waye M= 1.5 T=263 K 15 F- 40 KPa
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