Innovation of wind tunnel test by introducing multiobjective design exploration

• Project/Area Number: 26420129
• Research Category: Grant-in-Aid for Scientific Research (C)
• Allocation Type: Multi-year Fund
• Section: 一般
• Research Field: Fluid engineering
• Research Institution: Japan Aerospace EXploration Agency
• Principal Investigator: Oyama Akira 国立研究開発法人宇宙航空研究開発機構, 宇宙科学研究所, 准教授 (10373440)
• Project Period (FY): 2014-04-01 – 2017-03-31
• Project Status: Completed (Fiscal Year 2016)
• Budget Amount: ¥5,070,000 (Direct Cost: ¥3,900,000、Indirect Cost: ¥1,170,000); Fiscal Year 2016: ¥1,690,000 (Direct Cost: ¥1,300,000、Indirect Cost: ¥390,000); Fiscal Year 2015: ¥1,560,000 (Direct Cost: ¥1,200,000、Indirect Cost: ¥360,000); Fiscal Year 2014: ¥1,820,000 (Direct Cost: ¥1,400,000、Indirect Cost: ¥420,000)
• Keywords: 風洞試験 / 多目的設計探査 / 多目的設計最適化 / 流体制御 / プラズマアクチュエータ / 風洞実験 / 翼 / 進化計算 / 多目的最適化

Outline of Final Research Achievements

Purpose of this study is (1) Innovation of wind tunnel testing by introducing multiobjective design exploration used in combination with numerical simulation such as computational fluid dynamics into wind tunnel testing and (2) application of the proposed method to the wind tunnel testing of fluid control by the plasma actuator to clarify the influence of each parameter of the plasma actuator. Wind tunnel experiment based on multiobjective design exploration show its efficiency in parametric study. We also succeeded in obtaining useful information on the flow separation control around an airfoil by the plasma actuator.

Research Products

• [Presentation] 風洞試験に基づいたプラズマアクチュエータの多目的設計探査 (2016)
  • Author(s): 大山聖，Taufik Sulaiman, 野々村拓，藤井孝藏
  • Organizer: 最適化シンポジウム2016
  • Place of Presentation: 北海道札幌市札幌大学
  • Year and Date: 2016-12-06