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Title: Mach 2.8 turbulent boundary layer

Description: In this image, acetone droplet scattering is used to visualize streamwise cross-sections of a turbulent flat plate boundary layer at Mach 2.82 in streamwise wall-normal planes. The Reynolds number based on momentum thickness is about 82,000. The flow is from right to left, and the horizontal scale indicates the distance from the acetone injection point.

Credits: M. W. Smith* and Alexander J. Smits

References: Smith, M. W. and Smits, A. J., Visualization of the Structure of Supersonic Turbulent Boundary Layers. Experiments in Fluids 18, 288-302, 1995. *NASA Langley Research Center

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