Muhamad, Sallehuddin (2012) Wind tunnel testing of composite wing flutter speed due to control surface excitation. In: 3rd International Conference on Mechanical and Manufacturing Engineering 2012 (ICME2012), 20-21 November 2012, Malaysia.
Full text not available from this repository.
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) |
|---|---|
| Uncontrolled Keywords: | Control surface deflection, fiberglass composite tensile strength, flat plate wing composite, flutter frequency, flutter speed, wind tunnel testing |
| Subjects: | T Technology > TJ Mechanical engineering and machinery |
| Divisions: | Mechanical Engineering |
| ID Code: | 47821 |
| Deposited By: | Haliza Zainal |
| Deposited On: | 23 Jun 2015 03:05 |
| Last Modified: | 27 Aug 2017 05:03 |
Repository Staff Only: item control page
