Experimental study of the morphing flap as a low noise high lift device for aircraft wing

Yasuhiro Tani; Yoshiyuki Matsuda; Akira Doi; Yuya Yamashita; Shigeru Aso; Takeshi Ito

Experimental study of the morphing flap as a low noise high lift device for aircraft wing

Yasuhiro Tani, Yoshiyuki Matsuda, Akira Doi, Yuya Yamashita, Shigeru Aso, Takeshi Ito

宇宙システム工学

研究成果: Contribution to conference › Paper › 査読

1 被引用数 (Scopus)

抄録

To reduce the aeroacoustic noise of wings with high lift devices, a morphing flap configuration was proposed, which has smoothly contoured flap connected smoothly to the outer main wing. An wind tunnel test for NACA23012 wing model with interchangeable slotted flap was conducted in Kyushu university 2m × 2m Low-speed lownoise wind tunnel, at the condition of U=10 to 25m/s, Re=3.1 to 7.7×10⁵. Flap configurations tested were single slotted flap with deflection angle of 0 to 20 degrees and a morphing flap with deflection angle of 30 degrees at flap root smoothly contoured to 0 degree at flap edge section. Aeroacoustic noise was measured using phased array microphones and analyzed by the beamforming method. The measured results showed that the morphing flap has capability to suppress the flap side-edge noise and reduce the overall sound pressure level.

本文言語	英語
ページ	1042-1048
ページ数	7
出版ステータス	出版済み - 1 1 2012
イベント	28th Congress of the International Council of the Aeronautical Sciences 2012, ICAS 2012 - Brisbane, オーストラリア継続期間: 9 23 2012 → 9 28 2012

その他

その他	28th Congress of the International Council of the Aeronautical Sciences 2012, ICAS 2012
国/地域	オーストラリア
City	Brisbane
Period	9/23/12 → 9/28/12

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（全般）

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引用スタイル

Experimental study of the morphing flap as a low noise high lift device for aircraft wing. / Tani, Yasuhiro; Matsuda, Yoshiyuki; Doi, Akira; Yamashita, Yuya; Aso, Shigeru; Ito, Takeshi.

2012. 1042-1048 Paper presented at 28th Congress of the International Council of the Aeronautical Sciences 2012, ICAS 2012, Brisbane, オーストラリア.

研究成果: Contribution to conference › Paper › 査読

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title = "Experimental study of the morphing flap as a low noise high lift device for aircraft wing",

abstract = "To reduce the aeroacoustic noise of wings with high lift devices, a morphing flap configuration was proposed, which has smoothly contoured flap connected smoothly to the outer main wing. An wind tunnel test for NACA23012 wing model with interchangeable slotted flap was conducted in Kyushu university 2m × 2m Low-speed lownoise wind tunnel, at the condition of U=10 to 25m/s, Re=3.1 to 7.7×105. Flap configurations tested were single slotted flap with deflection angle of 0 to 20 degrees and a morphing flap with deflection angle of 30 degrees at flap root smoothly contoured to 0 degree at flap edge section. Aeroacoustic noise was measured using phased array microphones and analyzed by the beamforming method. The measured results showed that the morphing flap has capability to suppress the flap side-edge noise and reduce the overall sound pressure level.",

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year = "2012",

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T1 - Experimental study of the morphing flap as a low noise high lift device for aircraft wing

AU - Tani, Yasuhiro

AU - Matsuda, Yoshiyuki

AU - Doi, Akira

AU - Yamashita, Yuya

AU - Aso, Shigeru

AU - Ito, Takeshi

PY - 2012/1/1

Y1 - 2012/1/1

N2 - To reduce the aeroacoustic noise of wings with high lift devices, a morphing flap configuration was proposed, which has smoothly contoured flap connected smoothly to the outer main wing. An wind tunnel test for NACA23012 wing model with interchangeable slotted flap was conducted in Kyushu university 2m × 2m Low-speed lownoise wind tunnel, at the condition of U=10 to 25m/s, Re=3.1 to 7.7×105. Flap configurations tested were single slotted flap with deflection angle of 0 to 20 degrees and a morphing flap with deflection angle of 30 degrees at flap root smoothly contoured to 0 degree at flap edge section. Aeroacoustic noise was measured using phased array microphones and analyzed by the beamforming method. The measured results showed that the morphing flap has capability to suppress the flap side-edge noise and reduce the overall sound pressure level.

AB - To reduce the aeroacoustic noise of wings with high lift devices, a morphing flap configuration was proposed, which has smoothly contoured flap connected smoothly to the outer main wing. An wind tunnel test for NACA23012 wing model with interchangeable slotted flap was conducted in Kyushu university 2m × 2m Low-speed lownoise wind tunnel, at the condition of U=10 to 25m/s, Re=3.1 to 7.7×105. Flap configurations tested were single slotted flap with deflection angle of 0 to 20 degrees and a morphing flap with deflection angle of 30 degrees at flap root smoothly contoured to 0 degree at flap edge section. Aeroacoustic noise was measured using phased array microphones and analyzed by the beamforming method. The measured results showed that the morphing flap has capability to suppress the flap side-edge noise and reduce the overall sound pressure level.

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T2 - 28th Congress of the International Council of the Aeronautical Sciences 2012, ICAS 2012

Y2 - 22 September 2012 through 27 September 2012

ER -

Experimental study of the morphing flap as a low noise high lift device for aircraft wing

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