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Vorticity generation by contoured wall injectorsA class of contoured wall fuel injectors was designed to enable shock-enhancement of hypervelocity mixing for supersonic combustion ramjet applications. Previous studies of these geometries left unresolved questions concerning the relative importance of various axial vorticity sources in mixing the injectant with the freestream. The present study is a numerical simulation of two generic fuel injectors which is aimed at elucidating the relative roles of axial vorticity sources including: baroclinic torque through shock-impingement, cross-stream shear, turning of boundary layer vorticity, shock curvature, and diffusive flux. Both the magnitude of the circulation, and the location of vorticity with respect to the mixing interface were considered. Baroclinic torque and cross-stream shear were found to be most important in convectively mixing the injectant with the freestream, with the former providing for deposition of vorticity directly on the fuel/air interface.
Document ID
19920071422
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Waitz, Ian A.
(MIT Cambridge, MA, United States)
Marble, Frank E.
(NASA Langley Research Center Hampton, VA, United States)
Zukoski, Edward E.
(California Institute of Technology Pasadena, United States)
Date Acquired
August 15, 2013
Publication Date
July 1, 1992
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
AIAA PAPER 92-3550
Accession Number
92A54046
Funding Number(s)
CONTRACT_GRANT: NAG1-842
CONTRACT_GRANT: F49620-86-C-0113
Distribution Limits
Public
Copyright
Other

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