Composite wing flutter speed and frequency due to variable control surface deflection in low speed wind tunnel
Flutter is a dynamic instability problem represents the interaction among structural, aerodynamic, elastic and inertial forces and occurred when the energy is continuously transformed by the surrounding fluids to a flying structure in the form of kinetic energy. The study was conducted to investigat...
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| 主要な著者: | , , , |
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| フォーマット: | Conference or Workshop Item |
| 出版事項: |
2013
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| 主題: | |
| オンライン･アクセス: | http://eprints.utm.my/id/eprint/50954/ http://dx.doi.org/10.4028/www.scientific.net/AMM.390.3 |
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| 要約: | Flutter is a dynamic instability problem represents the interaction among structural, aerodynamic, elastic and inertial forces and occurred when the energy is continuously transformed by the surrounding fluids to a flying structure in the form of kinetic energy. The study was conducted to investigate the relationship of the control surface deflection angle to the flutter speed and the flutter frequency. A wind tunnel test was performed using a flat plate wing made of composite material. It was found that by deflecting the control surface up to 45°, the flutter speed reduced almost linearly from 35.6 m/s to 22.7 m/s. The flutter frequency greatly reduced from 48 Hz without the control surface deflected to 34 Hz with the control surface deflected at 15°. After 15° deflection up to 45°, the flutter frequency reduced almost linearly. |
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