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.
Shockwave/turbulent boundary layer interactions are studied by comparing direct numerical simulation and experimental data. Two canonical configurations, a 24-degree compression ramp and shock impinging a wall with reflection, are studied. The Mach number for the incoming boundary layer is 2.9. Re θ in the numerical simulation is 2400. Two experimental data sets are used, namely those of Bookey et al 1 at the same flow conditions as the DNS and those of Selig 2 at Re θ of about 70,000. Mean velocity profiles, wall pressure distribution, mass flux turbulence intensity, 2D density correlation and locations of the flow separation and reattachment are compared. In addition, an analysis of the turbulence structure characteristics for the DNS data is given.
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