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: 著書/レポートタイプへの貢献会議での発言

1 引用 (Scopus)

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.

元の言語英語
ホスト出版物のタイトル52nd AIAA Aerospace Sciences Meeting - AIAA Science and Technology Forum and Exposition, SciTech 2014
出版者American Institute of Aeronautics and Astronautics Inc.
ISBN(印刷物)9781624102561
出版物ステータス出版済み - 2014
イベント52nd AIAA Aerospace Sciences Meeting - AIAA Science and Technology Forum and Exposition, SciTech 2014 - National Harbor, MD, 米国
継続期間: 1 13 20141 17 2014

その他

その他52nd AIAA Aerospace Sciences Meeting - AIAA Science and Technology Forum and Exposition, SciTech 2014
米国
National Harbor, MD
期間1/13/141/17/14

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wind tunnel
Acoustic noise
wings
aircraft
Wind tunnels
Aeroacoustics
Microphones
Beamforming
wind tunnel tests
aeroacoustics
Acoustic waves
wing span
lift devices
configurations
low speed wind tunnels
lift coefficients
beamforming
phased arrays
noise measurement
sound pressure

All Science Journal Classification (ASJC) codes

  • Space and Planetary Science
  • Aerospace Engineering

これを引用

Tani, Y., Yamashita, Y., Miyazaki, K., Aso, S., Ura, H., & Ito, T. (2014). Morphing flap concept to reduce the flap side edge noise for aircraft wing slotted flaps. : 52nd AIAA Aerospace Sciences Meeting - AIAA Science and Technology Forum and Exposition, SciTech 2014 American Institute of Aeronautics and Astronautics Inc..

Morphing flap concept to reduce the flap side edge noise for aircraft wing slotted flaps. / Tani, Yasuhiro; Yamashita, Yuya; Miyazaki, Kazuma; Aso, Shigeru; Ura, Hiroki; Ito, Takeshi.

52nd AIAA Aerospace Sciences Meeting - AIAA Science and Technology Forum and Exposition, SciTech 2014. American Institute of Aeronautics and Astronautics Inc., 2014.

研究成果: 著書/レポートタイプへの貢献会議での発言

Tani, Y, Yamashita, Y, Miyazaki, K, Aso, S, Ura, H & Ito, T 2014, Morphing flap concept to reduce the flap side edge noise for aircraft wing slotted flaps. : 52nd AIAA Aerospace Sciences Meeting - AIAA Science and Technology Forum and Exposition, SciTech 2014. American Institute of Aeronautics and Astronautics Inc., 52nd AIAA Aerospace Sciences Meeting - AIAA Science and Technology Forum and Exposition, SciTech 2014, National Harbor, MD, 米国, 1/13/14.
Tani Y, Yamashita Y, Miyazaki K, Aso S, Ura H, Ito T. Morphing flap concept to reduce the flap side edge noise for aircraft wing slotted flaps. : 52nd AIAA Aerospace Sciences Meeting - AIAA Science and Technology Forum and Exposition, SciTech 2014. American Institute of Aeronautics and Astronautics Inc. 2014
Tani, Yasuhiro ; Yamashita, Yuya ; Miyazaki, Kazuma ; Aso, Shigeru ; Ura, Hiroki ; Ito, Takeshi. / Morphing flap concept to reduce the flap side edge noise for aircraft wing slotted flaps. 52nd AIAA Aerospace Sciences Meeting - AIAA Science and Technology Forum and Exposition, SciTech 2014. American Institute of Aeronautics and Astronautics Inc., 2014.
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abstract = "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.",
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