Numerical study of interaction of a jet with a supersonic cross flow

Weiguang Huang, Nobuhiko Yamasaki, Masanobu Namba

Research output: Contribution to journalArticle

Abstract

The paper presents FDM solutions of two-dimensional Navier-Stokes equations in a conservative-law form for a jet injected into a supersonic main flow. The effects of the jet-main flow pressure ratio, the injection angle and the injection flow Mach number on the jet-main flow interaction are studied. We also show a flow field where a rearward-facing step is placed upstream of the jet injection and the effects of the position of the step from the injection on the flow field. It is found that the boundary layer separation and the shock pattern caused by jet-main flow interaction are heavily dependent upon not only the injection flow Mach number but also the injection angle and the configuration of the rearward-facing step.

Original languageEnglish
Pages (from-to)467-488
Number of pages22
JournalMemoirs of the Kyushu University, Faculty of Engineering
Volume50
Issue number4
Publication statusPublished - Dec 1 1990

Fingerprint

jet flow
flow field
Flow interactions
Facings
Mach number
Navier-Stokes equations
Flow fields
Frequency division multiplexing
boundary layer
Supersonic flow
Navier Stokes equations
Boundary layers
Interaction
Injection
effect

All Science Journal Classification (ASJC) codes

  • Energy(all)
  • Atmospheric Science
  • Earth and Planetary Sciences(all)
  • Management of Technology and Innovation

Cite this

Numerical study of interaction of a jet with a supersonic cross flow. / Huang, Weiguang; Yamasaki, Nobuhiko; Namba, Masanobu.

In: Memoirs of the Kyushu University, Faculty of Engineering, Vol. 50, No. 4, 01.12.1990, p. 467-488.

Research output: Contribution to journalArticle

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