Exposed-Electrode Geometry Effects on DBD Plasma Actuation over Conical Forebody

2016 ◽  
Author(s):  
Duo Zhang ◽  
Xuanshi Meng ◽  
Haiyang Hu ◽  
Jianlei Wang ◽  
Feng Liu ◽  
...  
Keyword(s):  
Electrode Geometry ◽  
Dbd Plasma ◽  
Plasma Actuation ◽  
Geometry Effects

Plasma actuation effect on a NACA 4412 airfoil

2021 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Burak Karadag ◽  
Cem Kolbakir ◽  
Ahmet Selim Durna
Keyword(s):  
Reynolds Number ◽  
Flow Separation ◽  
Open Loop ◽  
Electrode Configuration ◽  
Small Scale ◽  
Low Velocity ◽  
Dbd Plasma ◽  
Content Type ◽  
Plasma Actuation ◽  
Electric Wind

Purpose This paper aims to investigate the effects of a dielectric barrier discharge (DBD) plasma actuator (PA) qualitatively on aerodynamic characteristics of a 3 D-printed NACA 4412 airfoil model. Design/methodology/approach Airflow visualization study was performed at a Reynolds number of 35,000 in a small-scale open-loop wind tunnel. The effect of plasma actuation on flow separation was compared for the DBD PA with four different electrode configurations at 10°, 20° and 30° angles of attack. Findings Plasma activation may delay the onset of flow separation up to 6° and decreases the boundary layer thickness. The effects of plasma diminish as the angle of attack increases. Streamwise electrode configuration, in which electric wind is produced in a direction perpendicular to the freestream, is more effective in the reattachment of the airflow compared to the spanwise electrode configuration, in which the electric wind and the free stream are in the same direction. Practical implications The Reynolds number is much smaller than that in cruise aircraft conditions; however, the results are promising for low-velocity subsonic airflows such as improving control capabilities of unmanned aerial vehicles. Originality/value Superior efficacy of spanwise-generated electric wind over streamwise-generated one is demonstrated at a very low Reynolds number. The results in the plasma aerodynamics literature can be reproduced using ultra-low-cost off-the-shelf components. This is important because high voltage power amplifiers that are frequently encountered in the literature may be prohibitively expensive especially for resource-limited university aerodynamics laboratories.

Investigation on the Effects of Field Emission Plasma on the Performance of a Micro-Combustor

2021 ◽  
Author(s):  
Maria Grazia De Giorgi ◽  
Giacomo Cinieri ◽  
Donato Fontanarosa ◽  
Antonio Ficarella
Keyword(s):  
Field Emission ◽  
Performance Enhancement ◽  
Plasma Chemistry ◽  
Plasma Discharge ◽  
Second Order ◽  
The Body ◽  
Coupling Scheme ◽  
Dbd Plasma ◽  
Reference Case ◽  
Plasma Actuation

Abstract This work provides a numerical investigation of the effects of micro field emission dielectric barrier discharge (FE-DBD) plasma actuation on the performance of a micro-combustion system composed of two straights perpendicular microchannels for propellant injection followed by a rectangular micro-combustion chamber in a T-shaped planar configuration. Concerning the modeling, a novel two-step approach has been developed. The first step consisted in solving the chemistry of a sinusoidal plasma discharge in a zero-dimensional modeling. To this purpose, the collisional processes involved in the plasma discharge have been solved using a Boltzmann-equation approach, which permits to predict the electron impact reactions based on a two-temperature model. Furthermore, the zero-dimensional hypothesis used for computations assumed uniform plasma during the overall discharge duration. Concerning the plasma chemistry, excitation and de-excitation processes, electron-ion recombination reactions, attachment and detachment for electrons and neutral species have been considered in order to improve the prediction accuracy. This step allowed to quantify the body force, the heat source and the propellant composition modification induced by sinusoidal plasma actuation operating at 10 MHz of repetition rate, atmospheric pressure and 300 K temperature. Therefore, the predicted cycle averaged plasma effects have been used in 2D steady-state simulations of the laminar, compressible, reactive micro flow, based on a continuum Navier-Stokes approach. SIMPLE pressure-velocity coupling scheme was chosen with a second order pressure spatial discretization. A second-order upwind scheme was applied. The hydrogen-oxygen combustion has been modeled using the Connaire mechanism. The comparison between the results of the reference case without plasma actuation, and those retrieved in presence of plasma actuation at different supplied voltages, highlighted the performance enhancement due to plasma discharge.

Parametric Study of Paraelectric and Peristaltic Pulsed DBD Plasma Actuation for Aerodynamic Flow Control Based on PIV

2017 ◽  
Vol 45 (4) ◽  
pp. 672-682 ◽  
Author(s):  
Feng Li ◽  
Chao Gao ◽  
Borui Zheng ◽  
Yushuai Wang ◽  
Zhe Lv ◽  
...  
Keyword(s):  
Flow Control ◽  
Parametric Study ◽  
Dbd Plasma ◽  
Plasma Actuation ◽  
Aerodynamic Flow Control

Magnetic field and electrode geometry effects on vehicle discharging by neutral gas release

1999 ◽  
Vol 104 (A11) ◽  
pp. 25159-25164
Author(s):  
D. N. Walker ◽  
R. F. Fernsler ◽  
W. E. Amatucci ◽  
D. Duncan ◽  
M. J. Keskinen
Keyword(s):  
Magnetic Field ◽  
Gas Release ◽  
Electrode Geometry ◽  
Neutral Gas ◽  
Geometry Effects
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