Test Section Turbulence in the AEDC/VKF Supersonic/Hypersonic Wind Tunnels
Final rept. 1 Oct 1979-30 Sep 1980
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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Free-stream fluctuation measurements were made in the 40-in. Supersonic Tunnel A at Mach numbers 1.5, 2, 3, 4, and 5 and in the 50-in. Hypersonic Tunnel B at Mach numbers 6 and 8 of the von Karman Gas Dynamics Facility, Arnold Engineering Development Center, using a hot-wire anemometer probe and a dynamic pitot pressure probe. Supplementary surface pressure fluctuation measurements were made on a flat plate model, on the surface of a slender cone model, and in Tunnel A on the stilling chamber and nozzle walls. The results are presented and discussed, and the anemometer and dynamic pitot pressure measurements are compared.
- Fluid Mechanics
- Non-Radio Communications