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

Research output: Chapter in Book/Report/Conference proceedingConference contribution


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.

Original languageEnglish
Title of host publication52nd Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Electronic)9781624102561
Publication statusPublished - Jan 1 2014
Event52nd Aerospace Sciences Meeting 2014 - National Harbor, United States
Duration: Jan 13 2014Jan 17 2014

Publication series

Name52nd Aerospace Sciences Meeting


Other52nd Aerospace Sciences Meeting 2014
Country/TerritoryUnited States
CityNational Harbor

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering


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