An experimental investigation was conducted to study four shock/turbulent boundary layer interactions. In Mach 2.9 flow, a 24º compression corner and a 12º reflected shock interaction were studied at Re θ = 2400. In a Mach 8 flow, an 8º compression corner and a 10º sharp fin were studied at Re θ = 3500. These low Reynolds number flows were chosen to coincide with DNS accessible Reynolds numbers in order to make direct comparisons. Measurements included mean flow surveys, surface pressure distributions, surface flow visualizations and Filtered Rayleigh Scattering (FRS). FRS was used to make twodimensional images of the flow in the streamwise direction giving a qualitative picture of the nature of the interaction. Statistical data of the boundary layer characteristics was also obtained from the FRS images. The results show the incoming boundary layer at both Mach numbers to be fully turbulent. The interactions in Mach 2.9 flow produced large areas of separation. The compression ramp in the Mach 8 flow was found to remain attached throughout the interaction, while the 10º sharp fin produced a large threedimensional separated region. The preliminary results indicate good agreement between experiment and DNS computations.

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