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Applications of Shock-Induced Mixing to Supersonic Combustion

Yang, Joseph and Kubota, Toshi and Zukoski, Edward E. (1993) Applications of Shock-Induced Mixing to Supersonic Combustion. AIAA Journal, 31 (5). pp. 854-862. ISSN 0001-1452. doi:10.2514/3.11696.

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Families of two-dimensional, unsteady shock-induced vortical flows are simulated numerically. The flows consist of one or more regions of light gas, surrounded by heavy gas, being overtaken by a normal shock wave. The interaction of the density gradient at each light/heavy interface with the pressure gradient from the shock wave generates vorticity. This causes the light gas regions to roll up into one or more counter-rotating vortex pairs, which stir and mix the light and heavy gases. The mixing is characterized by an asymptotic stretching rate. The effects of shock strength, light/heavy gas density ratio, and geometry on the mixing are investigated. These two-dimensional, unsteady flows are analogous to three-dimensional, steady flows that may be used in SCRAMJET combustors demanding rapid and efficient mixing of fuel and oxidizer. For such applications, 1) the fuel injectors should be elongated in the direction of the shock; 2) multiple smaller injectors are preferable to a single larger injector; 3) injectors should be arranged in groups of closely spaced pairs, rather than uniformly; and 4) multiple shock waves should be utilized, if possible.

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Additional Information:© 1992 American Institute of Aeronautics and Astronautics, Inc. Received Oct. 2, 1991; revision received Sept. 28, 1992; accepted for publication Oct. 8, 1992. This work was supported by the Air Force Office of Scientific Research, under the supervision of Julian Tishkoff, through Contract F49620-86-C-0113 and Grant AFOSR-90- 0188. It was also supported by the National Science Foundation through a Cray supercomputer grant at the San Diego Supercomputer Center. Joseph Yang was supported by the Office of Naval Research through an ONR Graduate Fellowship. The authors would like to thank Elaine S. Oran, of the Naval Research Laboratory, for providing the algorithm used in the numerical simulations.
Group:Guggenheim Jet Propulsion Center
Funding AgencyGrant Number
Air Force Office of Scientific Research (AFOSR)F49620-86-C-0113
Air Force Office of Scientific Research (AFOSR)AFOSR-90-0188
NSF/San Diego Supercomputer CenterUNSPECIFIED
Office of Naval Research (ONR)UNSPECIFIED
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Other Numbering System NameOther Numbering System ID
Guggenheim Jet Propulsion CenterUNSPECIFIED
Issue or Number:5
Record Number:CaltechAUTHORS:20101123-081927940
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Official Citation:Applications of shock-induced mixing to supersonic combustion YANG, JOSEPH;KUBOTA, TOSHI;ZUKOSKI, EDWARD E. (California Inst. of Technology, Pasadena) AIAA Journal (0001-1452) 1993 vol. 31 no. 5 pages 854-862
Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:20967
Deposited By: Ruth Sustaita
Deposited On:23 Nov 2010 17:55
Last Modified:09 Nov 2021 00:04

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