Vorticity Generation by Contoured Wall Injectors
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.
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.Attached Files
Published - 336_Waitz_IA_1992.pdf
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Additional details
- Eprint ID
- 20934
- Resolver ID
- CaltechAUTHORS:20101122-094355204
- NASA
- NAG 1-842
- Air Force Office of Scientific Research
- F49620-86-C-0113
- NSF
- NASA Ames NAS facilities
- JPL/Caltech Cray
- NASA Langley supercomputing facilities
- Created
-
2010-12-10Created from EPrint's datestamp field
- Updated
-
2019-10-03Created from EPrint's last_modified field
- Caltech groups
- Guggenheim Jet Propulsion Center
- Series Name
- AIAA Papers
- Series Volume or Issue Number
- 92-3550
- Other Numbering System Name
- AIAA
- Other Numbering System Identifier
- 92-3550