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- W2321727351 abstract "The interactions between shock-waves and turbulent boundary-layers in a Mach 2.5 wind tunnel have been visualized by a MHz-rate imaging system. The shock waves were produced by two-dimensional compression corners having angles of 14’ and 24”, and the flows were, respectively, attached and separated. At the compression corner, the sequential images clearly indicate the correlation between the shock motion and incoming turbulent boundary layer. Some large eddies in the boundary layer cause the shock to move in the streamwise direction for distances as large as the boundary layer thickness at a frequency as high as 100 kHz. Other eddies do not seem to effect the shock wave. The images also show the influence of the shock waves on the boundary layer structures. * Graduate Student, Mechanical & Aerospace Engineering, Student Member AIAA. ’ Professor, Mechanical & Aerospace Engineering, Associate Fellow AIAA. Copyright" @default.
- W2321727351 created "2016-06-24" @default.
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- W2321727351 date "2000-01-10" @default.
- W2321727351 modified "2023-09-26" @default.
- W2321727351 title "MHz rate visualization of separation shock structure" @default.
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- W2321727351 doi "https://doi.org/10.2514/6.2000-647" @default.
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