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Analysis of unsteady inviscid diffuser flow with a shock wave

Yang, V. and Culick, F. E. C. (1985) Analysis of unsteady inviscid diffuser flow with a shock wave. Journal of Propulsion and Power, 1 (3). pp. 222-228. ISSN 0748-4658.

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A finite difference scheme with a shock-fitting algorithm has been used to investigate unsteady inviscid now with a shock in an inlet diffuser. The flowfield consists of three different regions: the supersonic and the subsonic regions, and a region containing both air and liquid fuel droplets, separated by a normal shock wave and a fuel injection system. The analysis is based on a two-phase, quasi-one-dimensional model. The response of a shock wave to various disturbances has been studied, including large-amplitude periodic oscillations and pulse perturbations.

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Additional Information:© 1985 American Institute of Aeronautics and Astronautics. Received March 16, 1984; revision received Aug. 17, 1984. The authors are indebted to J. N. Levine for providing the updated numerical code for the self-adjusting hybrid scheme. This work represents a part of the results obtained from the research program supported partly by the California Institute of Technology and partly by the Air Force Office of Scientific Research, Grant AFOSR-80-0265.
Group:Guggenheim Jet Propulsion Center
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Air Force Office of Scientific Research (AFOSR)AFOSR-80-0265
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Guggenheim Jet Propulsion Center UNSPECIFIED
Record Number:CaltechAUTHORS:20110125-143851324
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Official Citation:Analysis of unsteady inviscid diffuser flow with a shock wave pages 222-228 YANG, V.;CULICK, F. E. C. (California Institute of Technology, Pasadena, CA) Journal of Propulsion and Power (0748-4658) 1985 vol. 1 no. 3
Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:21887
Deposited By: Ruth Sustaita
Deposited On:26 Jan 2011 17:06
Last Modified:25 Mar 2014 04:35

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