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.
| 元の言語 | 英語 |
|---|---|
| ページ | 1042-1048 |
| ページ数 | 7 |
| 出版物ステータス | 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 | オーストラリア |
| 市 | Brisbane |
| 期間 | 9/23/12 → 9/28/12 |
Fingerprint
All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Control and Systems Engineering
- Electrical and Electronic Engineering
- Materials Science(all)
これを引用
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 論文発表場所 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: 会議への寄与タイプ › 論文
}
TY - CONF
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.
UR - http://www.scopus.com/inward/record.url?scp=84896955632&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=84896955632&partnerID=8YFLogxK
M3 - Paper
AN - SCOPUS:84896955632
SP - 1042
EP - 1048
ER -