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Evaluation of turbulence reduction devices for the Langley 8-foot Transonic Pressure TunnelThe device test model consisted of a cooler, turning vanes, and settling chamber (immediately upstream of the contraction) in which various combinations of screens and honeycomb were tested. Conventional hot wires were used to measure the axial and lateral turbulence reduction for the different turbulence reduction devices. The final configuration chosen consisted of a honeycomb followed by five screens.
Document ID
19810015579
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Mckinney, M. O. (NASA Langley Research Center Hampton, VA, United States)
Scheiman, J. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
June 1, 1981
Subject Category
Research And Support Facilities (Air)
Report/Patent Number
NASA-TM-81792
L-14108
Report Number: NASA-TM-81792
Report Number: L-14108
Accession Number
81N24114
Funding Number(s)
PROJECT: RTOP 505-31-43-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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