A plasma actuator optimization study exploring the effects of geometric design and dielectric materials selection using thrust and power measurements

Summary form only given. An investigation has been made regarding the optimization of a single plasma actuator as a means of aerodynamic flow control for unmanned aerial vehicles (UAVs). Atmospheric pressure plasma actuators are simple electrohydrodynamic (EHD) devices that can be used to manipulate the boundary layer on a flight surface. As an example, they have been shown to alter the flow separation and stall characteristics of a wing. Reduction of the power required to operate a single actuator through maximization of the thrust-to-power ratio was the goal of this investigation. Force, velocity and power measurements were taken for a number of devices at a range of applied voltages, in quiescent air. The force measurement device was custom designed and fabricated, and accurately detects levels of force down to 0.05 mN. Optimized parameters include electrode geometry (i.e. upper and lower electrode width, position and spacing), dielectric material type and thickness, and applied voltage. Materials tested were quartz, printed circuit board (PCB), kapton, and silicone. Results show that the thrust to power ratio can be as much as doubled through this optimization