Numerical Study for Active Flow Control Using Dielectric Barrier Discharge Actuators
Publication: Journal of Aerospace Engineering
Volume 30, Issue 5
Abstract
This paper presents a numerical investigation of active aerodynamic flow control on an airfoil by dielectric barrier discharge plasma actuators. Simplified Maxwell equations for an electric field coupled with Navier-Stokes equations and turbulence models for fluid are implemented to simulate the wall jet flow induced by the body force attributable to the dielectric barrier discharge plasma actuators. The numerical model is validated with the laboratory results in the quiescent flow. The simulated maximum velocity in the quiescent environment is proportional to the applied voltage. The dielectric barrier discharge plasma actuators are also demonstrated to significantly influence the velocity profiles. The numerical model is applied to an airfoil with Reynolds number equal to , and the peak-to-peak voltage varies from 5 to 18 kV. The flow separation is delayed or removed to some extent by dielectric barrier discharge plasma at high angles of attack. The dielectric barrier discharge increases the lift coefficient, reduces the drag coefficient, and finally improves the performance of the airfoil.
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Information
Published In
Journal of Aerospace Engineering
Volume 30 • Issue 5 • September 2017
Copyright
©2017 American Society of Civil Engineers.
History
Received: Feb 6, 2015
Accepted: Mar 13, 2017
Published online: Jun 1, 2017
Published in print: Sep 1, 2017
Discussion open until: Nov 1, 2017
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