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

Research output: Contribution to conferencePaper

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.

Original languageEnglish
Pages1042-1048
Number of pages7
Publication statusPublished - Jan 1 2012
Event28th Congress of the International Council of the Aeronautical Sciences 2012, ICAS 2012 - Brisbane, Australia
Duration: Sep 23 2012Sep 28 2012

Other

Other28th Congress of the International Council of the Aeronautical Sciences 2012, ICAS 2012
CountryAustralia
CityBrisbane
Period9/23/129/28/12

Fingerprint

Wind stress
Aeroacoustics
Flow separation
Acoustic noise
Wind tunnels
Microphones
Beamforming
Acoustic waves

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Control and Systems Engineering
  • Electrical and Electronic Engineering
  • Materials Science(all)

Cite this

Tani, Y., Matsuda, Y., Doi, A., Yamashita, Y., Aso, S., & Ito, T. (2012). Experimental study of the morphing flap as a low noise high lift device for aircraft wing. 1042-1048. Paper presented at 28th Congress of the International Council of the Aeronautical Sciences 2012, ICAS 2012, Brisbane, Australia.

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, Australia.

Research output: Contribution to conferencePaper

Tani, Y, Matsuda, Y, Doi, A, Yamashita, Y, Aso, S & Ito, T 2012, 'Experimental study of the morphing flap as a low noise high lift device for aircraft wing' Paper presented at 28th Congress of the International Council of the Aeronautical Sciences 2012, ICAS 2012, Brisbane, Australia, 9/23/12 - 9/28/12, pp. 1042-1048.
Tani Y, Matsuda Y, Doi A, Yamashita Y, Aso S, Ito T. Experimental study of the morphing flap as a low noise high lift device for aircraft wing. 2012. Paper presented at 28th Congress of the International Council of the Aeronautical Sciences 2012, ICAS 2012, Brisbane, Australia.
Tani, Yasuhiro ; Matsuda, Yoshiyuki ; Doi, Akira ; Yamashita, Yuya ; Aso, Shigeru ; Ito, Takeshi. / Experimental study of the morphing flap as a low noise high lift device for aircraft wing. Paper presented at 28th Congress of the International Council of the Aeronautical Sciences 2012, ICAS 2012, Brisbane, Australia.7 p.
@conference{506a9326879948c4915692038f546db2,
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.",
author = "Yasuhiro Tani and Yoshiyuki Matsuda and Akira Doi and Yuya Yamashita and Shigeru Aso and Takeshi Ito",
year = "2012",
month = "1",
day = "1",
language = "English",
pages = "1042--1048",
note = "28th Congress of the International Council of the Aeronautical Sciences 2012, ICAS 2012 ; Conference date: 23-09-2012 Through 28-09-2012",

}

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 -