Development of active control method for wing noise based on highly efficient flow information reduction technique

2021 Fiscal Year Final Research Report

• Project/Area Number: 20K21043
• Research Category: Grant-in-Aid for Challenging Research (Exploratory)
• Allocation Type: Multi-year Fund
• Review Section: Medium-sized Section 24:Aerospace engineering, marine and maritime engineering, and related fields
• Research Institution: Tokyo University of Agriculture and Technology
• Principal Investigator: Kameda Masaharu 東京農工大学, 工学(系)研究科(研究院), 教授 (70262243)
• Co-Investigator(Kenkyū-buntansha): 中北 和之 国立研究開発法人宇宙航空研究開発機構, 航空技術部門, 主幹研究開発員 (50358595)
• Project Period (FY): 2020-07-30 – 2022-03-31
• Keywords: 航空宇宙工学 / 流体工学 / 熱流体力学 / 圧縮性流体

Outline of Final Research Achievements

An active noise control method based on data reduction technique has been developed for trailing edge noise (TE noise) of a two-dimensional airfoil. First, the TE noise input/output mode is identified by CFD and modal analysis, and a highly efficient noise suppression method based on this analysis is investigated. As a result, we have found that the noise is caused by two different mechanisms. One of the mechanism, the quadrupole noise due vortex interaction, has not been known before. It is also shown that the addition of a jet from the pressure side of the airfoil is effective in suppressing the noise. Next, from a wind tunnel test we have found that the newly discovered quadrupole noise indeed exists, and that adding a disturbance by a pulsed laser is effective in suppressing TE noise.

Free Research Field

航空宇宙工学

Academic Significance and Societal Importance of the Research Achievements

最先端のデータ科学をその特性を生かして流れ現象の把握，推定に適用し，その結果に基づく実現象の制御に本格的に取り組んだ．今回の対象である翼騒音も含め流体現象は，現象の特徴が支配方程式（NS方程式）の性質に内包されている．そのため，支配方程式の性質を考慮に入れたモード解析（レゾルベント解析）は，計算負荷，制御効果の最適化の点で，多数の教師データや計算量が要求される深層学習（deep learning）よりもはるかに優れている．実際，本研究により，そのようなモード解析に基づくプレデターミンド制御の有効性を示し，航空工学の発展，産業界の振興にも役立つ成果が得られた．