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• W2998187467 abstract "Experiments were conducted on a cylinder-induced shock wave boundary layer interaction (SBLI) as its state was brought through transition using a combination of boundary layer trips and Reynolds number sweep. A baseline case with no trips was also examined. The measurements were made in a Mach 6 freestream in the well-characterized Actively Controlled Expansion tunnel, which demonstrated a near tripling in fluctuation levels with a unit Reynolds number increase from 3.0 to 3.5 million per meter. Surface oil flow and schlieren images suggested the jump in freestream noise served as the impetus for SBLI transition since the flow separation distance began to decrease as the Reynolds number progressed through those conditions. Likewise, surface-mounted Kulite® pressure transducers indicated a rise in surface pressure fluctuations as well as initial growth in the instability responsible for transitioning the boundary layer within the interaction. Finally, heat transfer rates within the tripped SBLI were shown to be affected by the jump in freestream disturbance levels." @default.
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• W2998187467 date "2020-01-05" @default.
• W2998187467 modified "2023-09-23" @default.
• W2998187467 title "Some effects of tunnel noise on cylinder-induced Mach 6 transitional shock wave boundary layer interactions" @default.
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• W2998187467 doi "https://doi.org/10.2514/6.2020-0582" @default.
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