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Supersonic jet screech tone cancellationA new method of supersonic jet screech tone reduction is presented. The method utilizes a sound reflecting surface positioned upstream of the nozzle exit a distance of one-quarter wavelength of the fundamental screech tone. The reflector establishes a standing wave pattern of acoustic waves with a node at the nozzle exit plane. The pressure minimum at the exit halts the screech tone feedback mechanism. Experimental results indicate that the method eliminates supersonic jet screech as effectively as the currently accepted technique using an intrusive tab, but without distortion of the jet flow. The change in shock cell spacing, which occurs with an intrusive tab, does not occur when screech is cancelled with the new technique. The broadband shock-associated noise is also influenced much less when the jet screech tones are eliminated by the new method.
Document ID
19840027349
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Nagel, R. T.
(North Carolina State Univ. Raleigh, NC, United States)
Denham, J. W.
(North Carolina State Univ. Raleigh, NC, United States)
Papathanasiou, A. G.
(North Carolina State University Raleigh, NC, United States)
Date Acquired
August 12, 2013
Publication Date
November 1, 1983
Publication Information
Publication: AIAA Journal
Volume: 21
ISSN: 0001-1452
Subject Category
Acoustics
Accession Number
84A10136
Funding Number(s)
CONTRACT_GRANT: NAG3-189
Distribution Limits
Public
Copyright
Other

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