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Touchard 23 BFB BFB A.C. H.V. A.C. H.V. Figure 84. Upper view of the actuator with triangular electrodes. specific flow structures which will radically change the boundary layer in the required configuration. VI. CONCLUSION In this paper, the aerodynamic phenomena still faced by aeronautic industry have been first presented and the different control techniques or devices already used or tested in the past have been described. Then, a special focus has been put on plasma actuators. These actuators know recently (for about ten years) a very intense interest due to their fast response and their simple and robust conception. The development of such actuators has been possible with new technologies in plasma generation and flow analysis now available as well as a better understanding of electrical discharges behavior. From this overview of plasma actuators conceptions and working ways, it seems that the perspectives of such actuators in the field of aerodynamic control for aeronautics are to act on aerodynamic structures already existing in the boundary layer and to favor their enhancement in order to provoke the flow modifications required. REFERENCES [1] K. Takashima, N. Zouzou, E. Moreau, A. Mizuno and G. Touchard, "Generation of extended surface barrier discharge on dielectric surface – electrical properties", IJPEST, Vol. 1, No 1, pp. 14-20, 2007 [2] H. Schilchting, "Boundary layer theory", Mc Graw Hill, 1955 [3] R. Comolet, "Mécanique expérimentale des fluides", Masson, 1994 [4] A. Betz, "Verfahren zur direkten Ermittlung des profilwiderstandes", ZFM. 16, pp. 42, 1925 [5] B.M. Jones, ""The measurement of profile drag by the pitot traverse method", ARC R&M pp. 1688, 1936 [6] N. Jacobs, K.E. Ward, & R. M. Pinkerton, "The characteristics of 78 related airfoil sections from tests in the variable-density wind tunnel", NACA Report No. 460, 1933 [7] C. Wieselsberger, "Der Luftwiderstand von Kugeln" ZFM. 5, pp. 140-144, 1914 [8] M. Gad-el-Hak, "Flow control, passive, active and reactive flow management", Cambridge University Press, 2000 [9] M.J. Walsh and A. M. Lindemann, "Optimisation and Application of Riblets for Turbulent Drag Reduction", AIAA paper, No. 84-0347, 1984 [10] D.M. Bushnell and J. N. Hefner, "Viscous Drag Reduction in Boundary Layers", AIAA, 1990 [11] O. Schrenk, "Grenzschichtabsaugung", Luftwissen 7, 409, 1940 [12] E. Moreau, "Airflow control by non thermal plasma actuators", J. Phys. D: Appl. Phys. 40, pp. 605-636, 2007 [13] H. Velkoff and J. Ketcham, "Effect of an Electrostatic Field on Boundary-Layer Transition", AIAA J., 16, pp. 1381-1383, 1968 [14] M.R. Malik, L. Weinstein and M. Hussaini, "Ion Wind Drag Reduction", AIAA paper # 1983-0231, 1983 [15] F. Soetomo, "The influence of high voltage discharge on flat plate drag at low Reynolds number flow", M.S. thesis, Iowa States University, 1992 [16] F. Soetomo and G.M. Colver, "Effect of a corona discharge on boundary layer growth", Electostatics Society of America Conference, 1993 periodic ramp H.V. air stream Fig. 85. General view of the actuator with tungsten wire electrodes. V. DISCUSSION Most of the plasma actuators (apart the arc filament and the surface sliding arc) used the electric wind generated by the discharge. Looking at the specific velocity perform by all these actuators we notice that the maximum velocity realized, up to now, is in the order of 10 m/s and even often smaller. Thus, obviously, in the present state of plasma actuators development, actuation due to only a permanent blowing or suction with such actuators will never be able to reattach flow on a body flying at a transonic velocity. Then, the perspectives of these actuators are to generate instabilities which could enhance vortices already existing in the boundary layer and whose development could totally change the boundary layer structure. Indeed, the great advantage of this kind of actuators is their very fast response (Forte et al [60]). Thus, they can be used, as we have seen above, at a working frequency corresponding to the typical Strouhal number of the flow around the body experimented. In a near future it can be used at a right place, coupled with a sensor and acting at the right time in a special way to help the development ofPDF Image | Plasma actuators for aeronautics applications
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