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Measured response of a complex structure to supersonic turbulent boundary layersMeasurements of the response of a large frame-stringer panel excited by supersonic turbulent boundary layer are reported. The statistical description of the wall pressure fluctuations in terms of the mean flow parameters governing the turbulent boundary layer is given. These results can be used in the development of design criteria on the response of sidewall structure of a large airplane in supersonic flight, since both forcing field and structure are realistic. Results indicate the significant importance of the modal coupling and the acoustic damping. The acoustic damping plays a major role in the response of the structure.
Document ID
19760035814
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Maestrello, L.
(Air Force Flight Dynamics Lab. Wright-Patterson AFB, OH, United States)
Monteith, J. H.
(Air Force Flight Dynamics Lab. Wright-Patterson AFB, OH, United States)
Manning, J. C.
(NASA Langley Research Center Hampton, Va., United States)
Smith, D. L.
(USAF, Flight Dynamics Laboratory, Wright-Patterson AFB Ohio, United States)
Date Acquired
August 8, 2013
Publication Date
January 1, 1976
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 76-83
Meeting Information
Meeting: Aerospace Sciences Meeting
Location: Washington, DC
Start Date: January 26, 1976
End Date: January 28, 1976
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
76A18780
Distribution Limits
Public
Copyright
Other

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