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Acoustic Testing of a High-Tip-Speed Fan with Bypass-Duct Liners - OverviewUnder a pair of Space Act Agreements between NASA and Honeywell Aerospace, a model-scale (22 in.-diameter fan) acoustic wind tunnel test was carried out in the fall of 2014 in the NASA Glenn Research Center 9- by 15-Foot Low-Speed Wind Tunnel. The goal was to obtain acoustic pressure measurements for far-field, inlet and exit rotating rake, and in-duct microphone locations. This supersonic-tip-speed fan was tested in three bypass duct configurations: hard-wall, traditional liner, and advanced multiple-degree-of-freedom. Limited aerodynamic data was collected to verify the expected operating conditions. Preliminary analysis of the acoustic data finds it suitable for use in evaluating current NASA and Honeywell Aerospace acoustic tools and liner design practices. This report provides an overview of the test and some preliminary findings.
Document ID
20190025444
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Miller, Christopher J. (NASA Glenn Research Center Cleveland, OH, United States)
Stephens, David B. (NASA Glenn Research Center Cleveland, OH, United States)
Sutliff, Daniel L. (NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
May 31, 2019
Publication Date
May 1, 2019
Subject Category
Acoustics
Aerodynamics
Report/Patent Number
GRC-E-DAA-TN66525
NASA/TM-2019-220162
E-19678
Funding Number(s)
WBS: 081876.02.03.06
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Technical Review
Single Expert

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