GATE Aerospace Engineering 2011: Oblique Shock Wave Angle (Beta) for M=2 Compression Corner

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Aerospace Engineering > GATE 2011 > Oblique Shocks

Consider an inviscid, adiabatic flow of air at free stream Mach Number, M_∞ = 2, across a compression corner (θ = 20°) as shown. The free stream total enthalpy is h_∞ = 810 kJ kg^–1. Assume that air is calorically perfect with γ = 1.4, R = 287 J kg^–1 K^–1.

The shock angle β is

A

=20^o

B

> >20^o and <30^o

C

=30^o

D

>30^o

Correct : d

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Related Topics

GATE Aerospace Engineering 2011 GATE AE 2011 Q50 oblique shock wave compression corner shock angle shock angle beta gas dynamics supersonic flow Mach number compression corner

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