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Acoustic Treatment Design Scaling MethodsThe ability to design, build and test miniaturized acoustic treatment panels on scale model fan rigs representative of full scale engines provides not only cost-savings, but also an opportunity to optimize the treatment by allowing multiple tests. To use scale model treatment as a design tool, the impedance of the sub-scale liner must be known with confidence. This study was aimed at developing impedance measurement methods for high frequencies. A normal incidence impedance tube method that extends the upper frequency range to 25,000 Hz. without grazing flow effects was evaluated. The free field method was investigated as a potential high frequency technique. The potential of the two-microphone in-situ impedance measurement method was evaluated in the presence of grazing flow. Difficulties in achieving the high frequency goals were encountered in all methods. Results of developing a time-domain finite difference resonator impedance model indicated that a re-interpretation of the empirical fluid mechanical models used in the frequency domain model for nonlinear resistance and mass reactance may be required. A scale model treatment design that could be tested on the Universal Propulsion Simulator vehicle was proposed.
Document ID
20030063912
Acquisition Source
Langley Research Center
Document Type
Contractor Report (CR)
Authors
Clark, L.
(NASA Langley Research Center Hampton, VA, United States)
Parrott, T.
(NASA Langley Research Center Hampton, VA, United States)
Jones, M.
(NASA Langley Research Center Hampton, VA, United States)
Kraft, R. E.
(General Electric Aircraft Engines Cincinnati, OH, United States)
Yu, J.
(Goodrich (B. F.) Co. San Diego, CA, United States)
Kwan, H. W.
(Goodrich (B. F.) Co. San Diego, CA, United States)
Beer, B.
(Goodrich (B. F.) Co. San Diego, CA, United States)
Seybert, A. F.
(Kentucky Univ. Lexington, KY, United States)
Tathavadekar, P.
(Kentucky Univ. Lexington, KY, United States)
Date Acquired
September 7, 2013
Publication Date
January 7, 2003
Subject Category
Acoustics
Report/Patent Number
NAS 1.26:212428/PHASE2
NASA/CR-2003-212428/PHASE2
Funding Number(s)
WORK_UNIT: WU 781-30-14-01
CONTRACT_GRANT: NAS3-26617
Distribution Limits
Public
Copyright
Public Use Permitted.
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