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Aeroacoustic Experiments in the NASA Langley Low-Turbulence Pressure TunnelA phased microphone array was used in the NASA Langley Low-Turbulence Pressure Tunnel to obtain acoustic data radiating from high-lift wing configurations. The data included noise localization plots and acoustic spectra. The tests were performed at Reynolds numbers based on the cruise-wing chord, ranging from 3.6 x 10(exp 6) to 19.2 x 10(exp 6). The effects of Reynolds number were small and monotonic for Reynolds numbers above 7.2 x 10(exp 6).
Document ID
20020043801
Document Type
Technical Memorandum (TM)
Authors
Choudhari, Meelan M. (NASA Langley Research Center Hampton, VA United States)
Lockard, David P. (NASA Langley Research Center Hampton, VA United States)
Macaraeg, Michele G. (NASA Langley Research Center Hampton, VA United States)
Singer, Bart A. (NASA Langley Research Center Hampton, VA United States)
Streett, Craig L. (NASA Langley Research Center Hampton, VA United States)
Neubert, Guy R. (Boeing Commercial Airplane Co. Seattle, WA United States)
Stoker, Robert W. (Boeing Commercial Airplane Co. Seattle, WA United States)
Underbrink, James R. (Boeing Commercial Airplane Co. Seattle, WA United States)
Berkman, Mert E. (High Technology Corp. Hampton, VA United States)
Khorrami, Mehdi R. (High Technology Corp. Hampton, VA United States)
Date Acquired
September 7, 2013
Publication Date
February 1, 2002
Subject Category
Acoustics
Report/Patent Number
NASA/TM-2002-211432
L-18131
Funding Number(s)
PROJECT: RTOP 706-81-13-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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