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A systematic study of supersonic jet noise.The acoustic fields for a rectangular and for an axisymmetric nozzle configuration are studied. Both nozzles are designed for identical flow parameters. It is tried to identify the dominant noise mechanisms. The other objective of the study is to establish scaling laws of supersonic jet noise. A shock tunnel is used in the investigations. Measured sound directivity, propagation direction of Mach waves obtained by shadowgraphs, and the slight dependence of the acoustic efficiency on the level of expansion indicate that Mach waves contribute significantly to the noise produced by a rectangular jet.
Document ID
19720050425
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Louis, J. F.
Letty, R. P.
Patel, J. R. (MIT Cambridge, Mass., United States)
Date Acquired
August 6, 2013
Publication Date
June 1, 1972
Subject Category
Fluid Mechanics
Report/Patent Number
AIAA PAPER 72-641
Meeting Information
Meeting: American Institute of Aeronautics and Astronautics, Fluid and Plasma Dynamics Conference
Location: Boston, MA
Start Date: June 26, 1972
End Date: June 28, 1972
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
72A34091
Funding Number(s)
CONTRACT_GRANT: NGL-22-009-383
CONTRACT_GRANT: DOT-TSC-142
Distribution Limits
Public
Copyright
Other

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