Separation Control by Micro Plasma Actuator

2014 Fiscal Year Final Research Report

• Project/Area Number: 24560210
• Research Category: Grant-in-Aid for Scientific Research (C)
• Allocation Type: Multi-year Fund
• Section: 一般
• Research Field: Fluid engineering
• Research Institution: Tokyo University of Science
• Principal Investigator: ISHIKAWA Hitoshi 東京理科大学, 工学部, 教授 (90311521)
• Co-Investigator(Kenkyū-buntansha): HONAMI Shinji 東京理科大学, 工学部, 教授 (30089312)
• Co-Investigator(Renkei-kenkyūsha): SETO Takafumi 金沢大学, 自然システム学系, 教授 (40344155)
• Project Period (FY): 2012-04-01 – 2015-03-31
• Keywords: 流体制御 / アクチュエータ / プラズマ / はく離 / 翼

Outline of Final Research Achievements

The purpose of this study is to develop a micro plasma actuator as a new saving energy device for flow separation control. The size of the micro plasma actuator in which electrode is the order of under millimeter size is smaller than that of conventional type plasma actuator. First, the characteristics of the a micro plasma actuator was researched by flow visualization. The jet velocity was about 0.3 m/s in quiescent air. Wind tunnel measurement was performed to investigate the wake structure behind flat plate wing with straight type macro plasma actuator. Then we developed sine curved type micro plasma actuator which is possible to induce streamwise vortex by jet collision. The sine curve type macro plasma actuator was installed on the surface of NACA 0012 wing. It was confirmed that the energy consumption of the micro plasma actuator was lower than that of normal plasma actuator by using V-Q Lissajous method.

Free Research Field

流体工学