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Subsonic and supersonic jets and supersonic suppressor characteristics.The flow and acoustic characteristics over a Mach number range of 0.6 to 1.5 were determined for convergent and parallel flow nozzles with room temperature air. Mean velocity and fluctuating impact and static pressure distributions were investigated. Near- and far-field acoustic measurements were obtained, and overall sound power levels were compared with subsonic theory of Lighthill and supersonic theory of Nagamatsu and Horvay. Flow and acoustic characteristics of single and multiple shroud supersonic suppressors were studied. With 191 tubes and shrouds the overall sound power level for a Mach 1.4 jet was reduced 15.3 and 20.5 db respectively.
Document ID
19730060032
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Nagamatsu, H. T.
Sheer, R. E., Jr. (GE Research and Development Center Schenectady, N.Y., United States)
Date Acquired
August 7, 2013
Publication Date
October 1, 1973
Subject Category
Fluid Mechanics
Report/Patent Number
AIAA PAPER 73-999
Report Number: AIAA PAPER 73-999
Meeting Information
Meeting: Aero-Acoustics Conference
Location: Seattle, WA
Start Date: October 15, 1973
End Date: October 17, 1973
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
73A44834
Distribution Limits
Public
Copyright
Other

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