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.
|出版ステータス||出版済み - 1月 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月 23 2012 → 9月 28 2012
|その他||28th Congress of the International Council of the Aeronautical Sciences 2012, ICAS 2012|
|Period||9/23/12 → 9/28/12|
!!!All Science Journal Classification (ASJC) codes