Published 1985
| Published
Journal Article
Open
Analysis of unsteady inviscid diffuser flow with a shock wave
- Creators
- Yang, V.
- Culick, F. E. C.
Abstract
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.
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.Attached Files
Published - 313_Yang_v.pdf
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313_Yang_v.pdf
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Additional details
- Eprint ID
- 21887
- Resolver ID
- CaltechAUTHORS:20110125-143851324
- Caltech
- AFOSR-80-0265
- Air Force Office of Scientific Research (AFOSR)
- Created
-
2011-01-26Created from EPrint's datestamp field
- Updated
-
2019-10-03Created from EPrint's last_modified field
- Caltech groups
- Guggenheim Jet Propulsion Center, GALCIT
- Other Numbering System Name
- Guggenheim Jet Propulsion Center