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An experimental study of shock wave/vortex interactionThe interaction of a supersonic streamwise vortices (of Mach number 2.2, 3.0, and 3.5) with a normal shock wave has been experimentally investigated, and is found to be highly unsteady. Five-hole pressure-probe and temperature measurements ahead of the interaction are used as initial conditions for an axisymmetric Navier-Stokes calculation. The numerical results supports the hypothesis that supersonic vortex breakdown is an important factor in the observed interaction flow pattern.
Document ID
19890037701
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Metwally, O. M. (Pennsylvania State Univ. University Park, PA, United States)
Settles, G. S. (Pennsylvania State University University Park, United States)
Horstman, C. C. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1989
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 89-0082
Report Number: AIAA PAPER 89-0082
Accession Number
89A25072
Funding Number(s)
CONTRACT_GRANT: NCA2-235
Distribution Limits
Public
Copyright
Other

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