Hot-wire anemometry in subsonic slip and transonic flow regimes
Author:
Affiliation:
1. NASA, Langley Research Center, Hampton, VA
2. Old Dominion Univ., Norfolk, VA
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1994-2535
Reference17 articles.
1. Aerodynamic Noise in Supersonic Wind Tunnels
2. Wagner, R.D., and Weinstein, L.M., 1974, "Hot-Wire Anemometry in Hypersonic Helium Flow," NASA-TN-D-7465.
3. Morkovin, M.V., 1956,"Fluctucdionsand Hot-wire Anemometry in Compressible Flows," AGARDograph 24.
4. The Hot-Wire Anemometer in Supersonic Flow
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1. Experiment Researches on the Location of Transition Onset in the Hypersonic Wind Tunnel;48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition;2010-01-04
2. Reinvestigation of Hot-Wire Anemometry Applicable to Subsonic Compressible Flows Using Fluctuation Diagrams;Journal of Fluids Engineering;1995-06-01
3. A rational technique for calibrating hot-wire probes from subsonic to supersonic speeds;25th Plasmadynamics and Lasers Conference;1994-06-20
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