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Touchard 17 m/s air flow velocity, but the flow remained detach at 16° of attack angle. copper 0.0254 mm thick. A little overlap of 1 mm between these electrodes was set to ensure uniform plasma all along the electrodes (in the spanwise direction). The upstream electrode was stuck on the upper side of the dielectric (in contact with the airflow), while the downstream one was stuck on the lower side (figure 64). Fig. 64. The actuator configuration. Thus, with such arrangement, the actuators induced an electric wind velocity in the air stream direction. The actuators were directly bonded to the surface of the airfoil. The upstream actuator was placed exactly at the leading edge (0% of the cord), while the downstream one was placed near the trailing edge (90% of the cord). A special care was taken concerning the leading edge actuator in order to avoid any modification of the nose radius, thus, a special recess (0.1mm thick) was molded in the airfoil profile to ensure no change in the NACA profile. Experiments were made separately for the two actuators. The High voltage amplitude was from 7 to 11 kV peak to peak, the frequency used was between 3 and 5 kHz. In fact, two kinds of actuation was used, one call the steady one used directly the frequency of the source, the other one, called "unsteady" used the sinusoidal signal modulated by a square wave signal whose duty cycle could be adjusted (figure 65). The frequency of the square wave envelope was obviously much smaller than the frequency of the high voltage source. A.C. H.V. 12° Fig. 62. OAUGDP with eight actuators on a NACA 0015 airfoil. 4) SlatandflapasDBDactuators One of the most active groups in the field of non thermal plasma actuator for aeronautic applications is the group of T.C. Corke. They generally used DBD actuator on NACA profiles. As a rather recent example [47] of arrangement that they have used, we can see in figure 63 a NACA0015 profile experimented with two DBD actuators performed to reproduce the effects of a leading edge slat and a trailing edge flap on an airplane wing. Indeed, we have seen in § III.B.2, that the most common used devices on aircraft are slats, flaps and spoiler, the problem of such devices is that important, complex and heavy mechanisms are associated to them, to deploy and retract them, more they operate very slowly. Thus, replace these heavy devices by plasma actuator is an exciting goal. In the example above sited, T.C. Corke and his group made experiments on a NACA 0015 airfoil which had a 12.7 cm chord and a 30.48 cm span. Experiments were conducted in a wind tunnel for two air stream velocities: 21m/s and 30m/s. As they analyzed the changes in drag and lift on the airfoil, the airfoil was mounted on the support sting of a lift-drag force balance. duty unsteady period angle of attack periodic H.V. periodic H.V. Fig. 63. Leading edge and trailing edge actuators. They used DBD actuators made of two copper electrodes separated by two Kapton film layers (0.1 mm thick each of them). The electrodes were made with foil Fig. 65. High voltage modulation. Experiments using the leading edge actuator showed reattachment up to 19° angle of attack while normally flow separates around 14°, this for two air stream velocities (21m/s and 30m/s). Another important result is that, using unsteady actuation, the optimum unsteady copper foil electrodes Kapton layersPDF Image | Plasma actuators for aeronautics applications
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