Analysis of unsteady inviscid diffuser flow with a shock wave

V. Yang; F. E.C. Culickt

doi:10.2514/3.22784

Analysis of unsteady inviscid diffuser flow with a shock wave

V. Yang
, F. E.C. Culickt

College of Engineering

Research output: Contribution to journal › Article › peer-review

27 Citations (Scopus)

Abstract

A finite difference scheme with a shock-fitting algorithm has been used to investigate unsteady inviscid flow 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.

Original language	English
Pages (from-to)	222-228
Number of pages	7
Journal	Journal of Propulsion and Power
Volume	1
Issue number	3
DOIs	https://doi.org/10.2514/3.22784
Publication status	Published - 1985

All Science Journal Classification (ASJC) codes

Aerospace Engineering
Fuel Technology
Mechanical Engineering
Space and Planetary Science

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10.2514/3.22784

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abstract = "A finite difference scheme with a shock-fitting algorithm has been used to investigate unsteady inviscid flow 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.",

author = "V. Yang and Culickt, \{F. E.C.\}",

note = "Funding Information: 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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AU - Yang, V.

AU - Culickt, F. E.C.

N1 - Funding Information: 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.

PY - 1985

Y1 - 1985

N2 - A finite difference scheme with a shock-fitting algorithm has been used to investigate unsteady inviscid flow 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.

AB - A finite difference scheme with a shock-fitting algorithm has been used to investigate unsteady inviscid flow 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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Analysis of unsteady inviscid diffuser flow with a shock wave

Abstract

All Science Journal Classification (ASJC) codes

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