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Turbulence measurements in axisymmetric supersonic boundary layer flow in adverse pressure gradientsMean flow and turbulence measurements are presented for adiabatic compressible turbulent boundary layer flow in adverse pressure gradients. The gradients were induced on the wall of an axially symmetric wind tunnel by contoured centerbodies mounted on the wind tunnel centerline. The boundary layer turbulence downstream of a boundary layer bleed section in a zero pressure gradient was also examined. The measurements were obtained using a constant temperature hot-wire anemometer. The adverse pressure gradients were found to significantly alter the turbulence properties of the boundary layer. With flow through the bleed holes there was a measureable decrease in the rms longitudinal velocity fluctuations near the wall and the turbulent shear stress in the boundary layer was reduced.
Document ID
19770036994
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Gootzait, E.
(Pennsylvania State University University Park, Pa., United States)
Childs, M. E.
(Washington, University Seattle, Wash., United States)
Date Acquired
August 9, 2013
Publication Date
January 1, 1977
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 77-129
Meeting Information
Meeting: Aerospace Sciences Meeting
Location: Los Angeles, CA
Start Date: January 24, 1977
End Date: January 26, 1977
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
77A19846
Funding Number(s)
CONTRACT_GRANT: NGR-48-002-047
Distribution Limits
Public
Copyright
Other

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