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<p>An investigation was conducted to study four shock/turbulent boundary layer interactions. In Mach 2.9 flow, a 24 compression corner and a 12 reflected shock interaction were studied at Reynolds number based on momentum thickness = 2400. In Mach 8 flow, an 8 compression corner and a 10 sharp fin were studied at Reynolds number based on momentum thickness = 3500. The flow was examined through the use of surface oil flow visualization, surface pressure measurements, mean Pitot pressure and total temperature surveys and condensate-enhanced filtered Rayleigh scattering (FRS). The combination of these experimental techniques allowed the determination of velocity profiles, separation and reattachment points, mean surface pressure distribution, key surface features and provided information on the large-scale structures in the boundary layer through the shock interactions. The 24 compression corner interaction at Mach 2.9 produced a fully separated flow with the characteristic lengths of separation and mean pressure distribution significantly different than those of higher Reynolds numbers. The FRS images revealed a highly unsteady separation shock that was disturbed by passing large structures. The organized structures showed very little change through the interaction. The 12 reflected shock interaction produced the characteristics of a fully separated flow, with the height of the separation bubble on the order of the incoming boundary layer height. The point of intersection of the incident and separation shocks was unsteady. The 8 compression corner at Mach 8 was found to remain attached from surface oil flow visualizations, contrary to expectations. The shock wave was deeply entrained in the boundary layer and was highly distorted by passing large turbulent structures for several boundary layer thicknesses downstream of the corner. The 10 sharp fin interaction revealed the quasiconical symmetry of this type of interaction.
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<br>Subjects:</div>
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Bookey, Patrick B.</div>
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