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Published 1985 | Version Published
Journal Article Open

Analysis of unsteady inviscid diffuser flow with a shock wave

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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.

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Identifiers

Eprint ID
21887
Resolver ID
CaltechAUTHORS:20110125-143851324

Funding

Caltech
Air Force Office of Scientific Research (AFOSR)
AFOSR-80-0265

Dates

Created
2011-01-26
Created from EPrint's datestamp field
Updated
2019-10-03
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Caltech groups
Guggenheim Jet Propulsion Center , GALCIT
Other Numbering System Name
Guggenheim Jet Propulsion Center