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
Correct : d
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