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

1 Citation (Scopus)

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

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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.