Small current modulations in a subset of DIII-D I-coils were used in RMP ELM suppression experiments at ITER-like conditions (shape, collisionality, RMP spectrum) to control position of the divertor particle and heat fluxes. Qualitative agreement was found between measured HFS particle flux striations and modeling of magnetic footprints with and without ideal MHD plasma response. However, the radial separation of the particle flux striations is 4-7x larger than the modeled splitting. Striations are generally not observed in the divertor heat flux to the inner strike point in RMP ELM suppression at ITER-like conditions; this is understood to be due to an increase in the volumetric carbon radiation in the inner divertor which washes out the striations in the heat flux to the inner strike point. This suggests that radiative divertor operations in ITER may avoid striated peaks. The divertor target plate heat flux can be reduced 2–3x, with a 60% radiated power fraction, by establishing a narrow radiating mantle between 0.95 ≤ Ψ' ≤ 1. This is achieved without the loss of ELM suppression by using neon or argon injection into the main chamber. These radiating mantle discharges show for the first time that ELM suppression can be maintained over a wide range of pedestal collisionalities (0.1 < ν+ < 1.1) with only a modest increase in the line average electron density. IAEA-CN-258/EX/P6-17

The term "plasma actuator" has been a part of the fluid dynamics flow control vernacular for more than a decade. A particular type of plasma actuator that has gained wide use is based on a single dielectric barrier discharge (SDBD) mechanism that has desirable features for use in air at atmospheric pressures. For these actuators, the mechanism of flow control is through a generated body force vector that couples with the momentum in the external flow. The body force can be derived from first principles and the plasma actuator effect can be easily incorporated into flow solvers so that their placement and operation can be optimized. They have been used in a wide range of applications that include bluff body wake control; lift augmentation and separation control on a variety of lifting surfaces ranging from fixed wings with various degrees of sweep, wind turbine rotors and pitching airfoils simulating helicopter rotors; flow separation and tip-casing clearance flow control to reduce losses in turbines, to control flow surge and stall in compressors; and in exciting instabilities in boundary layers at subsonic to supersonic Mach numbers for turbulent transition control. New applications continue to appear through programs in a growing number of US universities and government laboratories, as well as in Germany, France, England, Netherland, Russia, Japan and China. This paper provides an overview of the physics, design and modeling of SDBD plasma actuators. It then presents their use in a number of applications that includes both numerical flow simulations and experiments together.

This paper provides an overview of the physics and design of single dielectric barrier discharge (SDBD) plasma actuators for enhanced aerodynamics in a variety of applications. The actuators consist of two electrodes, one exposed to the air and the other covered by a dielectric material. The electrodes are supplied with an ac voltage that at high enough levels, causes the air over the covered electrode to ionize. The ionization of the air is a dynamic process within the ac cycle. The ionized air, in the presence of the electric field produced by the electrode geometry, results in a body force vector that acts on the ambient air. The body force is the mechanism for active aerodynamic control. The body force per unit volume of plasma has been derived from first principles and implemented in numerical flow simulations. This utilizes models for the time and space dependence of the air ionization on the input voltage amplitude, frequency, electrode geometry and dielectric properties that have been developed and bench-marked with experiments. The experiments and model suggest approaches that can maximize the performance of the plasma actuators. A sample implementation of an actuator model in a numerical flow simulation consisting of leading-edge separation control on an airfoil along with an experimental benchmark is then presented.

This work presents the study of the single-dielectric barrier discharge aerodynamic plasma actuator. To model the physics of the plasma discharge, a space-time lumpedelement circuit model was developed. The model solution compared well to some of the characteristic features of the discharge such as the dependence of the sweep velocity and maximum extent of the ionized air as functions of the applied voltage and a.c. driving frequency. The time-dependent charge distribution obtained from the model was used to provide boundary conditions to the electric field equation that was used to calculate the time dependent electric potential. The was then used to calculate the space-time distribution of the actuator body force. An application of the plasma actuators to the leading-edge separation control on the NACA 0021 airfoil was studied numerically and experimentally. The results were obtained for a range of angles of attack for uncontrolled flow, and steady and unsteady plasma actuators located at the leading edge of the airfoil. The control of the lift stall was of particular interest. Improvement in the airfoil characteristics were observed in the numerical simulations at post-stall angles of attack with the plasma actuators. The computational results corresponded very well with the experiments.

The aerodynamic plasma actuator has shown considerable promise as a o w control device in dieren t applications. It has been shown previously that the lumped-element circuit model correctly describes the behavior of the aerodynamic plasma actuator. To incorporate this model into the Navier-Stokes solver, it was modied to include the spatial distribution of the discharge within the plasma. To model the behavior of the single dielectric barrier discharge aerodynamic plasma actuator, we represent it as a network of electric circuit elements. The electric circuit consists of N elementary subcircuits, each representing a small physical domain with nite width and length. Each subcircuit consists of the air capacitor, dielectric capacitor, plasma resistive element, and diodes which govern the presence of the plasma. The results of the simulation are compared to the experimental data of the plasma spatial distribution obtained with a photomultiplier tube.

The aerodynamic plasma actuator has shown considerable promise as a flow control device in different applications. A model for the plasma body force was created from the basic principles. To account for the spatial and temporal behavior of the plasma discharge the lumped-element circuit model was used. The objective of this work is to relate the numerical model to the experimental results qualitatively and quantitatively, demonstrating that plasma actuator thrust is proportional to voltage at the electrodes raised to the 7/2 power (Umax ∼ V ). The obtained results are utilized to lead to optimum designs that enhance the actuators effectiveness at producing unsteady disturbances as a means to prevent or delay boundary layer separation.