A Parametric Study to Explore ns-DBD Plasma Actuation for Aircraft Icing Mitigation

2018 ◽  
Author(s):  
Yang Liu ◽  
Cem Kolbakir ◽  
Hui Hu
Keyword(s):  
Parametric Study ◽  
Aircraft Icing ◽  
Dbd Plasma ◽  
Plasma Actuation

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

Parametric study of a DBD plasma actuation based on the Suzen-Huang model

2018 ◽  
Vol 93 ◽  
pp. 1-9 ◽  
Author(s):  
U.K. Seth ◽  
P. Traoré ◽  
F.J. Duran-Olivencia ◽  
E. Moreau ◽  
P.A. Vazquez
Keyword(s):  
Parametric Study ◽  
Dbd Plasma ◽  
Plasma Actuation

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.

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