Please use this identifier to cite or link to this item: http://hdl.handle.net/10397/10109
Title: Leading-edge surface-manipulated flow separation from an airfoil
Authors: Zhang, HJ
Zhou, Y
Issue Date: 2008
Publisher: Amer Inst Aeronaut Astronaut
Source: Journal of aircraft, 2008, v. 45, no. 6, p. 2171-2173 How to cite?
Journal: Journal of Aircraft 
Abstract: A method to control leading-edge surface-manipulated flow separation from an airfoil, is demonstrated. A Piezoelectric ceramic THUNDER actuators used for this method is placed at the suction side near the leading edge of the airfoil. A closed-circuit low-speed wind tunnel along with a 2.4-m-long square working section was used for this study. The airfoil used for this study is made of a slot of 0.07c in width on the upper surface and 0.08c downstream of the leading edge. A signal generator was also used to generate actuating sinusoidal signals, while a piezodriver amplifier was used for amplification. It was observed that the actuator and the thin plate can create a dynamically nonlinear system and its dynamic response depends on the activating frequency. The high-frequency perturbation is able to increase the static-stall angle of attack, which subsequently decrease the drag and increase the lift and lift-to-drag ratio.
URI: http://hdl.handle.net/10397/10109
ISSN: 0021-8669
DOI: 10.2514/1.36998
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