Clarifying Mach Number Effect for Supersonic Mixing and Developing Mixing Enhancement Device

2017 Fiscal Year Final Research Report

• Project/Area Number: 15K06605
• Research Category: Grant-in-Aid for Scientific Research (C)
• Allocation Type: Multi-year Fund
• Section: 一般
• Research Field: Aerospace engineering
• Research Institution: Osaka Prefecture University
• Principal Investigator: ARAI TAKAKAGE 大阪府立大学, 工学(系)研究科(研究院), 教授 (10175945)
• Co-Investigator(Kenkyū-buntansha): 坂上 昇史 大阪府立大学, 工学(系)研究科(研究院), 准教授 (70244655) ; 比江島 俊彦 大阪府立大学, 工学(系)研究科(研究院), 助教 (60316007)
• Project Period (FY): 2015-04-01 – 2018-03-31
• Keywords: スクラムジェット / 超音速混合 / 混合促進 / 超音速縦渦 / 渦崩壊

Outline of Final Research Achievements

For supersonic mixing enhancement in scramjet engine, streamwise vortices and its breakdown seem to be the most advantageous. In order to increase the mixing performance, it is important to introduce streamwise vortices which have larger circulation, and to enhance breakdown of them.
In the present study, we examined supersonic mixing field which is generated by ramp injector which has swept ramp angle, by Schlieren flow visualization, oil flow, and stereoscopic PIV method. It was confirmed that strength of streamwise vortices becomes stronger and they breakdown rapidly as the swept ramp angle decreases. And, we conducted the numerical simulations for the flow around the swept ramp device. The results clearly showed that the scale of the vortex region and the magnitude of the rotating speed increased as the swept ramp angle decreased. Finally, the swept ramp device which is proposed in the present study is effective for supersonic mixing on the case of the higher flight Mach number.

Free Research Field

航空宇宙工学