Analysis of unsteady inviscid diffuser flow with a shock wave

V. Yang, F. E.C. Culickt

Research output: Contribution to journalArticlepeer-review

25 Citations (Scopus)


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 languageEnglish
Pages (from-to)222-228
Number of pages7
JournalJournal of Propulsion and Power
Issue number3
Publication statusPublished - 1985

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Fuel Technology
  • Mechanical Engineering
  • Space and Planetary Science


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