Record Details

Wall Boundary Layer Measurements for the NASA Langley Transonic Dynamics Tunnel
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Author and Affiliation:
Wieseman, Carol D.(NASA Langley Research Center, Hampton, VA, United States);
Bennett, Robert M.(NASA Langley Research Center, Hampton, VA, United States)
Abstract: Measurements of the boundary layer parameters in the NASA Langley Transonic Dynamics tunnel were conducted during extensive calibration activities following the facility conversion from a Freon-12 heavy-gas test medium to R-134a. Boundary-layer rakes were mounted on the wind-tunnel walls, ceiling, and floor. Measurements were made over the range of tunnel operation envelope in both heavy gas and air and without a model in the test section at three tunnel stations. Configuration variables included open and closed east sidewall wall slots, for air and R134a test media, reentry flap settings, and stagnation pressures over the full range of tunnel operation. The boundary layer thickness varied considerably for the six rakes. The thickness for the east wall was considerably larger that the other rakes and was also larger than previously reported. There generally was some reduction in thickness at supersonic Mach numbers, but the effect of stagnation pressure, and test medium were not extensive.
Publication Date: Mar 01, 2007
Document ID:
20070019295
(Acquired Jun 13, 2007)
Subject Category: FLUID MECHANICS AND THERMODYNAMICS
Report/Patent Number: NASA/TM-2007-214867, L-19248
Document Type: Technical Report
Contract/Grant/Task Num: WBS 561581.02.08
Financial Sponsor: NASA Langley Research Center; Hampton, VA, United States
Organization Source: NASA Langley Research Center; Hampton, VA, United States
Description: 136p; In English; Original contains black and white illustrations
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: No Copyright
NASA Terms: BOUNDARY LAYERS; TRANSONIC WIND TUNNELS; WIND TUNNEL WALLS; TEST CHAMBERS; BOUNDARY LAYER THICKNESS; MACH NUMBER; SLOTS; STAGNATION PRESSURE; SUPERSONIC SPEED; FREON
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