Morphing flap concept to reduce the flap side edge noise for aircraft wing slotted flaps

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

研究成果: Chapter in Book/Report/Conference proceedingConference contribution

抄録

To reduce the aeroacoustic noise of wings with high lift devices, a morphing flap concept has been investigated, which has smoothly contoured flap connected smoothly to the outer main wing. Wind tunnel tests for NACA23012 half span wing model with flexible morphing slotted flap was conducted in Kyushu university 2m × 2m low-noise low-speed wind tunnel, at the condition of up to U= 40m/s, Re=1.3 × 106. Aeroacoustic noise measurement was carried out using phased array microphones and analyzed by the beamforming method. Three types of morphing flap configuration were compared with conventional single slotted flap. The wind tunnel test result showed that the morphing flap configuration suppress the flap side edge noise and lower overall sound pressure level with same level lift coefficient than conventional single slotted flap configurations.

本文言語英語
ホスト出版物のタイトル52nd Aerospace Sciences Meeting
出版社American Institute of Aeronautics and Astronautics Inc.
ISBN(電子版)9781624102561
出版ステータス出版済み - 1 1 2014
イベント52nd Aerospace Sciences Meeting 2014 - National Harbor, 米国
継続期間: 1 13 20141 17 2014

出版物シリーズ

名前52nd Aerospace Sciences Meeting

その他

その他52nd Aerospace Sciences Meeting 2014
Country米国
CityNational Harbor
Period1/13/141/17/14

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

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