Aerodynamic noise reduction for high lift devices using morphing flap concept

Yasuhiro Tani, Kazuma Miyazaki, Shigeru Aso, Hiroki Ura, Takeshi Ito

研究成果: 書籍/レポート タイプへの寄稿会議への寄与

1 被引用数 (Scopus)

抄録

To reduce the aeroacoustic noise of the aircraft wings with high lift devices, the morphing flap configurations, which has smoothly contoured flap surface connected smoothly to the outer main wing, were tested in 2m × 2m low-noise low-speed wind tunnel in Kyushu university. Wind tunnel test model is a half span wing model with a flexible morphing slotted flap part, at the flow condition of up to U= 40 m/s, Re=1.3 × 106. Aeroacoustic noise measurements were carried out using a phased array microphone system and beamforming method analysis, in addition to the aerodynamic force measurement. Four types of morphing flap configurations were compared with conventional single slotted flap configurations. The wind tunnel test result showed that the morphing flap configuration with small flap deflection at wing root section has both better high lift and lower noise characteristics, suppressing the flap side edge noise, than conventional single slotted flap configurations.

本文言語英語
ホスト出版物のタイトル29th Congress of the International Council of the Aeronautical Sciences, ICAS 2014
出版社International Council of the Aeronautical Sciences
ISBN(電子版)3932182804
出版ステータス出版済み - 2014
イベント29th Congress of the International Council of the Aeronautical Sciences, ICAS 2014 - St. Petersburg, ロシア
継続期間: 9月 7 20149月 12 2014

出版物シリーズ

名前29th Congress of the International Council of the Aeronautical Sciences, ICAS 2014

その他

その他29th Congress of the International Council of the Aeronautical Sciences, ICAS 2014
国/地域ロシア
CitySt. Petersburg
Period9/7/149/12/14

!!!All Science Journal Classification (ASJC) codes

  • 航空宇宙工学
  • 制御およびシステム工学
  • 電子工学および電気工学
  • 材料科学一般

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