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- W2031141451 abstract "A finite difference scheme with a shock-fitting algorithm has been used to investigate unsteady inviscid nowwith a shock in an inlet diffuser. The flowfield consists of three different regions: the supersonic and the subsonicregions, and a region containing both air and liquid fuel droplets, separated by a normal shock wave and afuel injection system. The analysis is based on a two-phase, quasi-one-dimensional model. The response of ashock wave to various disturbances has been studied, including large-amplitude periodic oscillations and pulseperturbations." @default.
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- W2031141451 title "Analysis of unsteady inviscid diffuser flow with a shock wave" @default.
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- W2031141451 doi "https://doi.org/10.2514/3.22784" @default.
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