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1894 LOPERA ET AL. 40-deg ramp will produce a strong separation; thus, the effect of the plasma actuator might not be strong enough to overcome the accompanying strong adverse pressure gradient. and inside the tunnel for in-plane views of the separation ramp and the aerodynamic plasma actuator. Flow visualization studies were conducted at flow conditions similar to the force measurements. The actuator was operated in an unsteady mode at a duty cycle of 12.5%. Figs. 17 and 18 show side-view visualizations of the inboard plasma actuator at 6 and 14 deg, respectively. The sequence of pictures shows that for the baseline case, the flow separates near the onset of the separation ramp. The tufts are observed to be lifted off the surface, which indicate a separated flowfield. When the plasma actuator is in operation, the tufts move very close to the wing surface. The movement of the tufts toward the surface is indicative of a reattachment of the flow close to the trailing-edge region. Figure 18 clearly shows the effect of the plasma actuator on the flow past the separationrampat14 deg.Thebaselineflowseparatesfromthe surface as it passes the separation ramp, and the pulsing of the plasma actuator causes the tufts (i.e., the flow) to reattach to the surface. Flow direction Flow direction Fig. 19 Planform-view sequence visualizations of inboard plasma actuator mounted at the onset of the windward-surface 20-deg separation ramp; plasma actuators pulsed with a 12.5% duty cycle, F 1, fmod 395 Hz, and 8- deg; (top) control off and (bottom) control on. Flow direction Flow direction Fig. 20 Planform-view sequence visualizations of inboard plasma actuator mounted at the onset of the windward-surface 20-deg separation ramp; plasma actuators pulsed with a 12.5% duty cycle, F 1, fmod 395 Hz, and 14- deg; (top) control off and (bottom) control on. B. Flow Visualization Investigations Flow visualization studies were conducted to corroborate the force balance data and to gain additional insights into the flow physics associated with the use of a SDBD plasma actuator at the onset of a windward-surface separation ramp near the trailing edge. Flow visualizations were performed by placing arrays of tufts over the plasma actuator and onto the separation ramp. Flow visualizations were captured via a video camera, and the videos were later edited to extract snapshot images of the baseline and controlled cases. The videos were captured at the standard 30 frames-per-second rate. The camera was placed outside of the tunnel for side views of the wing Separated flow r egion P lasma off off Control off Flow direction Control on Flow direction Plasma on Attached flow region Separated flow region Fig. 17 mounted at the onset of windward-surface 20-deg separation ramp; plasma actuators pulsed with a 12.5% duty cycle, F 1, fmod 395 Hz, and 6- deg; (top) control off and (bottom) control on. Control off Flow direction Control on Flow direction Side-view sequence visualizations of inboard plasma actuator Fig. 18 mounted at the onset of the windward-surface 20-deg separation ramp; plasma actuators pulsed with a 12.5% duty cycle, F 1, fmod 395 Hz, and 14- deg; (top) control off and (bottom) control on. Side-view sequence visualizations of inboard plasma actuator Separated flow region Control off Attached flow region Control on Attached flow region Separated flow region Control off Attached flow region Control onPDF Image | Aerodynamic Control Using Windward-Surface Plasma Actuators on a Separation Ramp
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