An investigation of a contoured wall injector for hypervelocity mixing augmentation
Abstract
An experimental and computational investigation of a contoured wall fuel injector is presented. The injector was aimed at enabling shock-enhanced mixing for the supersonic combustion ramjet engines currently envisioned for applications on hypersonic vehicles. Three-dimensional flow field surveys, and temporally resolved planar Rayleigh scattering measurements are presented for Mach 1.7 helium injection into Mach 6 air. These experimental data are compared directly with a three-dimensional Navier-Stokes simulation of the flow about the injector array. Two dominant axial vorticity sources are identified and characterized. The axial vorticity produced strong convective mixing of the injectant with the freestream. Shock-impingement was particularly effective as it assured seeding of baroclinic vorticity directly on the helium/air interface. The vorticity coalesced into a counter-rotating vortex pair of a sense which produced migration of the helium away from the wall. The influences of spatial averaging on the representation of the flow field as well as the importance of the fluctuating component of the flow in producing molecularly-mixed fluid are addressed.
Additional Information
© 1991 American Institute of Aeronautics and Astronautics, Inc. All rights reserved. For permission to copy or republish, contact American Institute of Aeronautics and Astronautics. Funding for this work was provided largely through NASA Grant NAG 1-842. The authors wish to thank many members of the technical staff at NASA Langley Research Center. particularly Dennis Bushnell. members of the Experimental Flow Physics Branch, and members of the Computational Methods Branch. The Rayleigh scattering data were obtained through a collaborative effort with B. Shirinzadeh. J. Balla. M. Hillard and R. Exton of the Instrument Research Division's Optical Spectroscopy Section. 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 - 321_Waitz_IA_1991.pdf
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Additional details
- Eprint ID
- 21058
- Resolver ID
- CaltechAUTHORS:20101130-101649129
- NAG 1-842
- NASA
- NSF
- 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
- AIAA 91-2265
- Other Numbering System Name
- AIAA
- Other Numbering System Identifier
- 91-2265