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Vorticity Generation by Contoured Wall Injectors

Waitz, Ian A. and Marble, Frank E. and Zukoski, Edward E. (1992) Vorticity Generation by Contoured Wall Injectors. AIAA Papers, 92-3550. American Institute of Aeronautics and Astronautics . http://resolver.caltech.edu/CaltechAUTHORS:20101122-094355204

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Abstract

A 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 fue1/air interface.


Item Type:Report or Paper (Report)
Additional Information:© 1992 American Institute of Aeronautics and Astronautics, Inc. Funding for this work was provided largely through NASA Grant NAG 1-842. The fundamentals of shock-enhanced mixing were developed earlier under Contract F49620-86-C- 0113 administered by the Air Force Office of Scientific Research. The authors wish to thank many members of the technical staff at NASA Langley Research Center, particularly D. Bushnell, S. Robinson, M. Walsh, members of the Experimental Flow Physics Branch, and members of the Computational Methods Branch. Supercomputing support was provided by the San Diego Supercomputer Center via a National Science Foundation Grant, the NASA Ames NAS facilities, the JPL/Caltech Cray, and the NASA Langley supercomputing facilities.
Group:Guggenheim Jet Propulsion Center
Funders:
Funding AgencyGrant Number
NASANAG 1-842
Air Force Office of Scientific ResearchF49620-86-C-0113
NSFUNSPECIFIED
NASA Ames NAS facilitiesUNSPECIFIED
JPL/Caltech CrayUNSPECIFIED
NASA Langley supercomputing facilitiesUNSPECIFIED
Other Numbering System:
Other Numbering System NameOther Numbering System ID
Guggenheim Jet Propulsion CenterUNSPECIFIED
AIAA92-3550
Record Number:CaltechAUTHORS:20101122-094355204
Persistent URL:http://resolver.caltech.edu/CaltechAUTHORS:20101122-094355204
Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:20934
Collection:CaltechAUTHORS
Deposited By: Ruth Sustaita
Deposited On:10 Dec 2010 00:09
Last Modified:26 Dec 2012 12:40

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