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Computing Jet Screech: a Complex Aeroacoustic Feedback SystemThe space-time conservation-element and solution-element method is employed to numerically study the near-field axisymmetric screech-tone noise of a typical underexpanded circular jet issuing from a sonic nozzle. For the computed case, corresponding to a fully expanded Mach number of 1.19, the self-sustained feedback loop is established without artificial means. The computed shock-cell structure, acoustic wave length, screech tone frequency, and sound pressure levels are in good agreement with existing experimental results
Document ID
20020081288
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Loh, Ching Y. (Taitech, Inc. Brook Park, OH United States)
Hultgren, Lennart S. (NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
September 7, 2013
Publication Date
August 1, 2002
Subject Category
Aeronautics (General)
Report/Patent Number
NAS 1.15:211807
NASA/TM-2002-211807
E-13502
Meeting Information
Meeting: Second International Conference on Computational Fluid Dynamics
Location: Sydney
Country: Australia
Start Date: July 15, 2002
End Date: July 19, 2002
Sponsors: Sydney Univ., Dassault Aviation, Institution of Engineers, NASA Headquarters, Defence Science and Technology Organisation
Funding Number(s)
PROJECT: RTOP 708-90-43
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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