Aerospace Engineering > GATE 2015 > Normal Shock Waves
For a normal shock, the relation between the upstream Mach number (M1) and the downstream Mach number (M2) is given by M22=((γ-1)M12+2)/(2γM12+1-γ) For an ideal gas with γ=1.4 the asymptotic value of the downstream Mach number is
Correct : 0.37 to 0.39
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