Turbulence measurements in a compressible boundary layer subjected to a shock-wave-induced adverse pressure gradient
Author:
Affiliation:
1. NASA, Ames Research Center, Moffett Field, Calif.
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1973-167
Reference10 articles.
1. Fluctuation Measurements in a Supersonic Turbulent Boundary Layer
2. Boundary-layer Pitot and hot-wire surveys at a free-stream Mach number of about 20
3. 6rande,E."An Investigation of the Unsteady Flow Properties of the Interaction Between a Shock Wave a Turbulent Boundary Layer in Two-Dimensional Internal Flow," Ph.D. Thesis,University of Washiagton, 1971.
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