Turbulence measurements in a Mach 11 helium boundary layer
Author:
Affiliation:
1. NASA, Langley Research Center, Hampton, VA
2. Syracuse Univ., NY
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1994-2364
Reference31 articles.
1. [l]Alving, A. E. 1988 "Boundary Layer Relaxation from Convex Curvature," Ph.D. Thesis,Department of Mechanical & Aerospace Engineering, Princeton University.
2. Determination and optimization of frequency response of constant temperature hot‐wire anemometers in supersonic flows
3. Reynolds Stress Measurements in a Hypersonic Boundary Layer
4. Fernando, E. M. 1988 "Supersonic Turbulent Boundary Layer in an Adverse Pressure Gradient," Ph.D. Thesis,Department of Mechanical & Aerospace Engineering, Princeton University.
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2. Tripping of a Hypersonic Low-Reynolds-Number Boundary Layer;AIAA Journal;2017-03
3. Direct numerical simulation of hypersonic turbulent boundary layers. Part 3. Effect of Mach number;Journal of Fluid Mechanics;2011-03-02
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