MACH 2.8 TURBULENT BOUNDARY LAYER
M. W. Smith* and Alexander J. Smits
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
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