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Touchard 1 Plasma actuators for aeronautics applications - State of art review- G. Touchard Laboratoire d'Etudes Aérodynamiques, Boulevard Marie et Pierre Curie, BP 30179, 86962 Futuroscope Cedex, France Abstract - The goal of this paper is to make a detailed review of the designs and associated setups of the different aerodynamic plasma actuators developed these last twenty years. First, some basic aspects of aerodynamic and their consequences in aeronautics are exposed. Then, the different aerodynamic conventional and plasma actuators are presented. Finally, the limits and the prospects of plasma actuators considered for airflow control are discussed. Keywords - Air flow control, plasma actuators. I. INTRODUCTION It is now well known and many papers have already been published in the "International Journal of Plasma Environmental Science & Technology" (IJPEST), that non thermal plasma can be used for environmental applications; even some joint research between our laboratory and the "Department of Ecological Engineering" of Toyohashi University of Technology, Japan, has already been made concerning surface barrier discharge and specially sliding discharge [1]. This paper concerns another environmental purpose using plasma applications: the fuel consumption reduction or air planes enhancing the aerodynamic flow control with plasma actuators. Recent researches and developments on aerodynamic plasma actuators is due to the conjunction of a technological need in aerodynamic control to be used in aeronautic industry and new investigations on aerodynamic properties of plasma actuators. In order to understand the reasons of the recent important development of researches on plasma actuators it is first important to know the technological need in air flow control for aeronautic applications. II. TECHNOLOGICALNEEDINAIRFLOWCONTROLFOR AERONAUTIC APPLICATIONS This paragraph deals with the basic knowledge which is needed to understand the aerodynamic phenomena that has to face aeronautic industry. Most of the results presented here are well developed in two reference books written by Schlichting [2], and Comolet [3]. A. Aerodynamicforces A plate placed perpendicular to an air flow is submitted to a force which push the plate in the same direction that the flow (figure 1). It is due to the difference between the total pressures on the two sides of the plate. Indeed, behind the plate the pressure is lower due to the detachment of the flow. In aeronautics this force is generally called the drag. If the plate is inclined (figure 2) the force has a vertical component. In aeronautics this component is called the lift. Finally an airfoil, which can correspond for instance to the wings of an airplane, moving from right to left is generally submitted to two different forces: one from left to right (so in the opposite direction of the motion) called the drag and one from bottom to top called the lift (figure 3). high pressure low pressure drag low pressure Fig. 1. Force on a vertical plate submitted to a flow. Fig. 2. Force on an inclined plate submitted to a flow. Aerodynamique force airfoil drag motion lift Corresponding author: G. Touchard e-mail address: Gerard.Touchard@lea.univ-poitiers.fr Received; January 16, 2008, Accepted; March 18, 2008 Fig. 3. Drag and lift on an airfoil submitted to a flow.PDF Image | Plasma actuators for aeronautics applications
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