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Wall Boundary Layer Measurements for the NASA Langley Transonic Dynamics TunnelMeasurements 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.
Document ID
20070019295
Document Type
Technical Memorandum (TM)
Authors
Wieseman, Carol D. (NASA Langley Research Center Hampton, VA, United States)
Bennett, Robert M. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 23, 2013
Publication Date
March 1, 2007
Subject Category
Fluid Mechanics and Thermodynamics
Report/Patent Number
L-19248
NASA/TM-2007-214867
Funding Number(s)
WBS: WBS 561581.02.08
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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