Laser Velocimeter and Hot-wire Anemometer Comparison in a Supersonic Boundary Layer
Author:
Affiliation:
1. NASA Ames Research Center, Moffet Field, Calif.
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/3.49739
Reference10 articles.
1. Turbulence Measurements in a Mach 2.9 Boundary Layer Using Laser Velocimetry
2. Rose, W. C. "The Behavior of a Compressible Turbulent Boundary Layer in a Shock-Wave-Induced Adverse Pressure Gradient," Ph.D. thesis,1972, Dept. of Mechanical Engineering, Universityof Washington, Seattle, Washington (available as TN D-7092, NASA).
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