Parametric study of burst mode on vortex structure induced by DBD plasma actuator

2019 ◽  
Author(s):  
Ming Xue ◽  
Chao Gao ◽  
Feng Liu ◽  
Shijun Luo
Keyword(s):  
Vortex Structure ◽  
Parametric Study ◽  
Plasma Actuator ◽  
Dbd Plasma ◽  
Burst Mode

Turbulent Boundary Layer Separation Control by Using DBD Plasma Actuators: Part II—Numerical Model Validation and Parametric Study

2010 ◽  
Author(s):  
Xiaofei Xu ◽  
Huu Duc Vo ◽  
Njuki Mureithi ◽  
Xue Feng Zhang
Keyword(s):  
Boundary Layer ◽  
Turbulent Boundary Layer ◽  
Parametric Study ◽  
Boundary Layer Separation ◽  
Plasma Actuator ◽  
Plasma Actuators ◽  
Low Flow ◽  
Dbd Plasma ◽  
Layer Separation ◽  
Flow Velocities

Following an experimental investigation into suppression of a 2-D turbulent boundary layer separation with dielectric barrier discharge (DBD) plasma actuators, the present work investigates the concept numerically. The purpose is to develop and validate a simulation tool that captures the flow physics and carry out a parametric study of the concept at flow regimes beyond the current flow control capability of plasma actuators of conventional strength. First, a plasma actuator model is integrated into the commercial computational fluid dynamics (CFD) code ANSYS CFX to simulate the effects of plasma actuation. This computational tool is validated through comparison of results with the experimental results for pulsed actuation in quiescent air and for the control of a turbulent boundary layer separation at low flow velocities. It is shown that CFX with an integrated plasma model can capture the main experimentally observed effects of DBD actuators on turbulent boundary layer separation. Subsequently, this numerical approach is used, with increased plasma actuator strength, to study the influence of different actuation parameters (e.g., actuation location, direction and frequency) on suppression of turbulent boundary layer separation at higher flow velocities.

Computational Study of Aerodynamic Characteristics of an Airfoil With DBD Plasma Actuator

2011 ◽  
Author(s):  
Kengo Asada ◽  
Kozo Fujii
Keyword(s):  
Computational Study ◽  
Lift Coefficient ◽  
Leading Edge ◽  
Aerodynamic Characteristics ◽  
Plasma Actuator ◽  
Separation Control ◽  
Vortex Center ◽  
Dbd Plasma ◽  
Burst Frequency ◽  
Burst Mode

The relation between aerodynamic characteristics and the effectiveness of separation control with the DBD plasma actuator over the airfoil are discussed. The flow-fields around the NACA0015 airfoil are simulated with implicit large-eddy simulation using compact difference scheme. The normal mode generates moderately separated region over the airfoil and gains lift by negative pressure at the vortex center. The burst mode with nondimensional burst frequency of 1 enhances the vortex shedding from the separation shear layer and avoid the massive separation from the leading edge. However, the lift coefficient oscillate very much, in this case. The burst mode with nondimensional burst frequency of 6 improves the airfoil performance by suppressing the separation region. These facts indicate that the unsteady aerodynamic characteristics must be discussed when the effectiveness of separation control is evaluated.

Formation and characterization of the vortices generated by a DBD plasma actuator in burst mode

2017 ◽  
Vol 29 (2) ◽  
pp. 024104 ◽  
Author(s):  
Bal Krishan Mishra ◽  
P. K. Panigrahi
Keyword(s):  
Plasma Actuator ◽  
Dbd Plasma ◽  
Burst Mode

Experimental Study of Blowing Direction Effects of DBD Plasma Actuator on Separation Control of Flow Around an Airfoil

2011 ◽  
Author(s):  
Taku Nonomura ◽  
Satoshi Sekimoto ◽  
Kengo Asada ◽  
Akira Oyama ◽  
Kozo Fujii
Keyword(s):  
Boundary Layer ◽  
Experimental Study ◽  
Normal Mode ◽  
Separated Flow ◽  
Plasma Actuator ◽  
Velocity Fields ◽  
Separation Control ◽  
Dbd Plasma ◽  
Burst Mode ◽  
Piv Measurement

An experimental study of plasma actuator on separation control is conducted. The plasma actuator is used for control of separated flow around NACA0015 airfoil. The Reynolds number based on chord length is set to 60,000 and the angle of attack is set to 12[deg]. The plasma actuator is applied with normal mode and burst mode, where normal mode denotes continuous actuation and burst mode denotes temporary intermittent actuation. Also, actuations for co-flow blowing and counter blowing are conducted. The averaged pressure coefficients of wing surface and velocity fields are measured. For velocity fields, PIV measurement is adopted. Comparing counter and co-flow blowings of plasma actuator, the effects of counter blowing is investigated. Also, for both co-flow and counter blowing cases, we investigate the effects of burst mode. Through the series of experiments, following two types of mechanism for separation control will be discussed. One type is considered to be directly giving momentum in the boundary layer which seems to be more active in co-flow blowing with normal mode. The other type is considered to be enhancement of the mixing, leading to increase in momentum thickness of the boundary layer. The latter mechanism seems to be active in the burst mode with both co-flow and counter blowing.

scholarly journals Surface velocity model of the flow caused by a DBD plasma actuator

2019 ◽  
Vol 85 (869) ◽  
pp. 18-00368-18-00368 ◽  
Author(s):  
Keunseob LEE ◽  
Satoshi KIKUCHI ◽  
Shigeki IMAO
Keyword(s):  
Velocity Model ◽  
Plasma Actuator ◽  
Surface Velocity ◽  
Dbd Plasma

Wall Normal Jet Produced by DBD Plasma Actuator With Doughnut-Shaped Electrode

2008 ◽  
Author(s):  
Takehiko Segawa ◽  
Hiro Yoshida ◽  
Shinya Takekawa ◽  
Timothy Jukes ◽  
Kwing-So Choi
Keyword(s):  
Atmospheric Pressure ◽  
Room Temperature ◽  
Particle Image ◽  
Barrier Discharge ◽  
Plasma Actuator ◽  
Dbd Plasma ◽  
Annular Jet ◽  
Image Velocimetry ◽  
Inner Diameter ◽  
Annular Jets

Properties of coaxial annular jets produced by a dielectric barrier discharge (DBD) plasma actuator with a doughnut shaped electrodes were investigated under atmospheric pressure and room temperature. The actuator consists of two circular electrodes sandwiching a thin dielectric layer. By applying 0 – ±3.3 kV between the electrodes at radio frequencies, the plasma jet is formed near the inner edge of the top electrode. The radial jet runs toward the center of the electrode and then impinges at the center to generate a wall normal annular jet. The evolution of the wall normal jet was observed precisely using particle image velocimetry (PIV) system. It was found that characteristic velocities increase in proportion to the bursting frequency and inversely proportional to the inner diameter of the electrode at the surging time of the voltage at 5.0 × 10−6sec.

Design Exploration of a DBD Plasma Actuator for Massive Separation Control

2015 ◽  
Author(s):  
Takeshi Watanabe ◽  
Hikaru Aono ◽  
Tomoaki Tatsukawa ◽  
Taku Nonomura ◽  
Akira Oyama ◽  
...  
Keyword(s):  
Plasma Actuator ◽  
Separation Control ◽  
Dbd Plasma ◽  
Design Exploration ◽  
Massive Separation
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