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An LDA (Laser-Doppler Anemometry) investigation of three-dimensional normal shock wave boundary-layer interactionsNonintrusive measurements were made of a normal shock wave/boundary layer interaction. Two dimensional measurements were made throughout the interaction region while 3-D measurements were made in the vicinity of the shock wave. The measurements were made in the corner of the test section of a continuous supersonic wind tunnel in which a normal shock wave had been stabilized. Laser Doppler Anemometry, surface pressure measurement and flow visualization techniques were employed for two freestream Mach number test cases: 1.6 and 1.3. The former contained separated flow regions and a system of shock waves. The latter was found to be far less complicated. The results define the flow field structure in detail for each case.
Document ID
19890011585
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Chriss, R. M. (NASA Lewis Research Center Cleveland, OH, United States)
Hingst, W. R. (NASA Lewis Research Center Cleveland, OH, United States)
Strazisar, A. J. (NASA Lewis Research Center Cleveland, OH, United States)
Keith, T. G., Jr. (Toledo Univ. OH., United States)
Date Acquired
September 5, 2013
Publication Date
March 1, 1989
Publication Information
Publication: NASA, Langley Research Center, Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 2
Subject Category
Aerodynamics
Accession Number
89N20956
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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