Abstract
To reduce the aeroacoustic noise of the aircraft wings with high lift devices, the morphing flap configurations, which has smoothly contoured flap surface connected smoothly to the outer main wing, were tested in 2m × 2m low-noise low-speed wind tunnel in Kyushu university. Wind tunnel test model is a half span wing model with a flexible morphing slotted flap part, at the flow condition of up to U= 40 m/s, Re=1.3 × 106. Aeroacoustic noise measurements were carried out using a phased array microphone system and beamforming method analysis, in addition to the aerodynamic force measurement. Four types of morphing flap configurations were compared with conventional single slotted flap configurations. The wind tunnel test result showed that the morphing flap configuration with small flap deflection at wing root section has both better high lift and lower noise characteristics, suppressing the flap side edge noise, than conventional single slotted flap configurations.
| Original language | English |
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| Title of host publication | 29th Congress of the International Council of the Aeronautical Sciences, ICAS 2014 |
| Publisher | International Council of the Aeronautical Sciences |
| ISBN (Electronic) | 3932182804 |
| Publication status | Published - 2014 |
| Event | 29th Congress of the International Council of the Aeronautical Sciences, ICAS 2014 - St. Petersburg, Russian Federation Duration: Sept 7 2014 → Sept 12 2014 |
Other
| Other | 29th Congress of the International Council of the Aeronautical Sciences, ICAS 2014 |
|---|---|
| Country/Territory | Russian Federation |
| City | St. Petersburg |
| Period | 9/7/14 → 9/12/14 |
All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Control and Systems Engineering
- Electrical and Electronic Engineering
- Materials Science(all)