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

Download Full-text

Characterization of DBD plasma actuator with ZnO nanowire arrays

Nanotechnology ◽

10.1088/1361-6528/abd35a ◽

2020 ◽

Author(s):

Haitao Wang ◽

Zhongyu Hou ◽

Changlin Li ◽

Bo Wang

Keyword(s):

Plasma Actuator ◽

Nanowire Arrays ◽

Zno Nanowire ◽

Dbd Plasma ◽

Zno Nanowire Arrays

Download Full-text

Characterization of efficiency of energy deposition of a ns-DBD plasma actuator

54th AIAA Aerospace Sciences Meeting ◽

10.2514/6.2016-1212 ◽

2016 ◽

Cited By ~ 1

Author(s):

Jakob Van den Broecke ◽

Giuseppe Correale ◽

Francesco Avallone

Keyword(s):

Energy Deposition ◽

Plasma Actuator ◽

Dbd Plasma

Download Full-text

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

ASME-JSME-KSME 2011 Joint Fluids Engineering Conference: Volume 1, Symposia – Parts A, B, C, and D ◽

10.1115/ajk2011-15010 ◽

2011 ◽

Cited By ~ 1

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.

Download Full-text