An experimental study of the interaction between supersonic streamwise vortex and two-dimensional oblique shock was conducted to investigate the application of vortex/oblique shock interaction in supersonic combustion.The strong/moderate/weak interactions at different shock strengths were observed in the experiment using color-schlieren method.The numberical results agree with the experiments.Experimental results show that

for the case of Ma=2.3

10 degrees wing attack angle

vortex is strong

and as wedge compress angle increases the vortex/oblique shock interaction changes from weak to strong interaction.Numberical results indicate that for the same wing and wedge situation

Mach number has strong influence on vortex/shock wave interaction.Total temperature can affect the size of the bubble shock.The effect of total pressure is neglectable.