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.
|ジャーナル||Memoirs of the Kyushu University, Faculty of Engineering|
|出版ステータス||出版済み - 12 1 1990|
All Science Journal Classification (ASJC) codes