An experimental investigation has been made in various supersonic and hypersonic wind tunnels at VKI to determine the effect of Mach number on the existence of stream wise vortices in the reattachment region of the flow over two-dimensional backward facing steps. It was found that the phenomenon previously observed at M = 2.21 remained unchanged over a Mach number range of 1.5 to 7.0. The ratio of the wave length of the vortices to the boundary layer thickness at separation varied slightly with free stream Mach number. with a maximum at about M = 3 .
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