Universiti Teknologi Malaysia Institutional Repository

Wind tunnel testing of composite wing flutter speed due to control surface excitation

Iyas, M. M. and Sallehuddin, M. and Sukri, M. A. M. and Shuhaimi, M. M. (2013) Wind tunnel testing of composite wing flutter speed due to control surface excitation. In: Applied Mechanics And Materials.

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Official URL: http://dx.doi.org/10.4028/www.scientific.net/AMM.3...

Abstract

Flutter is a dynamic instability problem represents the interaction among aerodynamic forces and structural stiffness during flight. The study was conducted to investigate whether deflecting the control surface will affect 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 at 45°, the wing entered flutter state at wind speed of 28.1 m/s instead of 33.4 m/s. In addition, the flutter frequency also reduced from 224.52 Hz to 198.96 Hz. It was concluded that by deflecting the control surface, the wing experienced flutter at lower speed and frequency.

Item Type:Conference or Workshop Item (Paper)
Subjects:T Technology > TL Motor vehicles. Aeronautics. Astronautics
Divisions:Others
ID Code:51399
Deposited By: Haliza Zainal
Deposited On:27 Jan 2016 09:53
Last Modified:18 Sep 2017 11:02

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