PIV measurement of separation flow control around airfoil using nanosecond-pulse driven plasma actuator

2016 ◽  
Vol 2016 (0) ◽  
pp. 0304
Author(s):  
Naoki TANAKA ◽  
Kaiki KONNO ◽  
Atsushi KOMURO ◽  
Keisuke TAKASHIMA ◽  
Akira ANDO ◽  
...  
Keyword(s):  
Flow Control ◽  
Plasma Actuator ◽  
Nanosecond Pulse ◽  
Separation Flow ◽  
Piv Measurement

Flow-Control Characteristics with Nanosecond-Pulse Plasma Actuator for Different Airfoil Shapes

AIAA Journal ◽  
2021 ◽  
pp. 1-9
Author(s):  
Atsushi Komuro ◽  
Shoki Kanno ◽  
Kento Suzuki ◽  
Akira Ando ◽  
Taku Nonomura ◽  
...  
Keyword(s):  
Flow Control ◽  
Plasma Actuator ◽  
Nanosecond Pulse ◽  
Pulse Plasma

scholarly journals Coherent structures induced by dielectric barrier discharge plasma actuator

2017 ◽  
Vol 31 (32) ◽  
pp. 1850038 ◽  
Author(s):  
Xin Zhang ◽  
Huaxing Li ◽  
Kwing So Choi ◽  
Longfei Song
Keyword(s):  
Flow Control ◽  
Dielectric Barrier Discharge ◽  
Coherent Structures ◽  
High Speed ◽  
Barrier Discharge ◽  
Plasma Actuator ◽  
Dbd Plasma ◽  
Peak Voltage ◽  
Dielectric Barrier ◽  
Piv Measurement

The structures of a flow field induced by a plasma actuator were investigated experimentally in quiescent air using high-speed Particle Image Velocimetry (PIV) technology. The motivation behind was to figure out the flow control mechanism of the plasma technique. A symmetrical Dielectric Barrier Discharge (DBD) plasma actuator was mounted on the suction side of the SC (2)-0714 supercritical airfoil. The results demonstrated that the plasma jet had some coherent structures in the separated shear layer and these structures were linked to a dominant frequency of [Formula: see text] = 39 Hz when the peak-to-peak voltage of plasma actuator was 9.8 kV. The high speed PIV measurement of the induced airflow suggested that the plasma actuator could excite the flow instabilities which lead to production of the roll-up vortex. Analysis of transient results indicated that the roll-up vortices had the process of formation, movement, merging and breakdown. This could promote the entrainment effect of plasma actuator between the outside airflow and boundary layer flow, which is very important for flow control applications.

Flow control over swept wings using nanosecond-pulse plasma actuator

2016 ◽  
Vol 61 ◽  
pp. 58-67
Author(s):  
Kentaro Kato ◽  
Christian Breitsamter ◽  
Shinnosuke Obi
Keyword(s):  
Flow Control ◽  
Plasma Actuator ◽  
Nanosecond Pulse ◽  
Pulse Plasma ◽  
Swept Wings

1105 Separation Flow Control Using Deflected Jet by a Trielectrode Plasma Actuator

2012 ◽  
Vol 2012.50 (0) ◽  
pp. 110501-110502
Author(s):  
Mikimasa KAWAGUCHI ◽  
Noboru FUJITA ◽  
Kousuke SUZUKI ◽  
Takashi MATSUNO ◽  
Gouji YAMADA ◽  
...  
Keyword(s):  
Flow Control ◽  
Plasma Actuator ◽  
Separation Flow

Experimental Study of Flow Control Over a Standard Road Vehicle Using Plasma Actuator

2020 ◽  
Vol 22 (4) ◽  
pp. 1047-1060
Author(s):  
S. Shadmani ◽  
S. M. Mousavi Nainiyan ◽  
R. Ghasemiasl ◽  
M. Mirzaei ◽  
S. G. Pouryoussefi
Keyword(s):  
Flow Control ◽  
Pressure Distribution ◽  
Drag Force ◽  
Separated Flow ◽  
Plasma Actuator ◽  
Road Vehicle ◽  
Slant Angle ◽  
Total Drag ◽  
Slant Surface ◽  
Ahmed Body

AbstractAhmed Body is a standard and simplified shape of a road vehicle that's rear part has an important role in flow structure and it's drag force. In this paper flow control around the Ahmed body with the rear slant angle of 25° studied by using the plasma actuator system situated in middle of the rear slant surface. Experiments conducted in a wind tunnel in two free stream velocities of U = 10m/s and U = 20m/s using steady and unsteady excitations. Pressure distribution and total drag force were measured and smoke flow visualization carried out in this study. The results showed that at U = 10m/s using plasma actuator suppress the separated flow over the rear slant slightly and be effective on pressure distribution. Also, total drag force reduces in steady and unsteady excitations for 3.65% and 2.44%, respectively. At U = 20m/s, using plasma actuator had no serious effect on the pressure distribution and total drag force.

scholarly journals Wing flow control using pulse thermal plasma actuator

2018 ◽  
Author(s):  
A. A. Kornyakov ◽  
A. V. Voevodin ◽  
D. A. Petrov ◽  
A. S. Petrov ◽  
G. G. Soudakov
Keyword(s):  
Flow Control ◽  
Thermal Plasma ◽  
Plasma Actuator
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