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A wind tunnel application of large-field focusing schlierenA large-field focusing schlieren apparatus was installed in the NASA Lewis Research Center 9 by 15 foot wind tunnel in an attempt to determine the density gradient flow field of a free jet issuing from a supersonic nozzle configuration. The nozzle exit geometry was designed to reduce acoustic emissions from the jet by enhancing plume mixing. Thus, the flow exhibited a complex three-dimensional structure which warranted utilizing the sharp focusing capability of this type of schlieren method. Design considerations concerning tunnel limitations, high-speed photography, and video tape recording are presented in the paper.
Document ID
19930035149
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Ponton, Michael K. (NASA Langley Research Center Hampton, VA, United States)
Seiner, John M. (NASA Langley Research Center Hampton, VA, United States)
Mitchell, L. K. (NASA Langley Research Center Hampton, VA, United States)
Manning, James C. (NASA Langley Research Center Hampton, VA, United States)
Jansen, Bernard J. (NASA Langley Research Center Hampton, VA, United States)
Lagen, Nicholas T. (Lockheed Engineering and Sciences Co. Hampton, VA, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Publication Information
Publication: In: DGLR(AIAA Aeroacoustics Conference, 14th, Aachen, Germany, May 11-14, 1992, Proceedings. Vol. 1 (A93-19126 05-71)
Publisher: Deutsche Gesellschaft fuer Luft- und Raumfahrt
Subject Category
Acoustics
Accession Number
93A19146
Distribution Limits
Public
Copyright
Other

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