Leading-Edge Separation Control Using Alternating-Current and Nanosecond-Pulse Plasma Actuators

AIAA Journal ◽  
2014 ◽  
Vol 52 (9) ◽  
pp. 1871-1884 ◽  
Author(s):  
Christopher L. Kelley ◽  
Patrick O. Bowles ◽  
John Cooney ◽  
Chuan He ◽  
Thomas C. Corke ◽  
...  
Keyword(s):  
Leading Edge ◽  
Alternating Current ◽  
Nanosecond Pulse ◽  
Plasma Actuators ◽  
Pulse Plasma ◽  
Separation Control ◽  
Edge Separation

High Lift Airfoil Leading Edge Separation Control with Nanosecond Pulse DBD Plasma Actuators

2010 ◽  
Author(s):  
Jesse Little ◽  
Keisuke Takashima ◽  
Munetake Nishihara ◽  
Igor Adamovich ◽  
Mo Samimy
Keyword(s):  
Leading Edge ◽  
Nanosecond Pulse ◽  
Plasma Actuators ◽  
Separation Control ◽  
Dbd Plasma ◽  
High Lift ◽  
Edge Separation

Experimental Study of Separation Control Over a Wide Range of Reynolds Numbers Using Dielectric Barrier Discharge Plasma Actuator on Airfoil

2017 ◽  
Author(s):  
Satoshi Sekimoto ◽  
Kozo Fujii ◽  
Masayuki Anyoji ◽  
Yuma Miyakawa ◽  
Shinichiro Ito ◽  
...  
Keyword(s):  
Dielectric Barrier Discharge ◽  
Barrier Discharge ◽  
Leading Edge ◽  
Reynolds Numbers ◽  
Plasma Actuator ◽  
Chord Length ◽  
Separation Control ◽  
Dielectric Barrier ◽  
Wide Range ◽  
Edge Separation

This study proposes separation control investigation using a Dielectric Barrier Discharge (DBD) plasma actuator on a NACA0015 airfoil over a wide range of Reynolds numbers. The airfoil was a two dimensional NACA0015 wing model with chord length of 200mm. Reynolds numbers based on the chord length were ranged from 252,000 to 1,008,000. A plasma actuator was installed at the leading edge and driven with AC voltage. Burst mode (duty cycle) actuations, in which nondimensional burst frequency F+ was ranged in 0.1–30, were applied. Time-averaged pressure measurements were conducted with angles of attack from 14deg to 22deg. The results show that initial flow fields without an actuation can be classified into three types; 1) leading edge separation, 2) trailing edge separation, and 3) hysteresis condition between 1) and 2), and the effect of burst actuation is different for each above initial condition.

Flow Control on a Transport Truck Side Mirror Using Plasma Actuators

2015 ◽  
Vol 137 (11) ◽  
Author(s):  
Theodoros Michelis ◽  
Marios Kotsonis
Keyword(s):  
Flow Control ◽  
Guide Vane ◽  
Leading Edge ◽  
Plasma Actuator ◽  
Plasma Actuators ◽  
Dbd Plasma ◽  
Reference Case ◽  
Image Velocimetry ◽  
Wind Tunnel Study ◽  
Edge Separation

A wind tunnel study is conducted toward hybrid flow control of a full scale transport truck side mirror at ReD=3.2×105. A slim guide vane is employed for redirecting high-momentum flow toward the mirror wake region. Leading edge separation from the guide vane is reduced or eliminated by means of an alternating current -dielectric barrier discharge (AC-DBD) plasma actuator. Particle image velocimetry (PIV) measurements are performed at a range of velocities from 15 to 25 m/s and from windward to leeward angles from -5deg to 5deg. Time-averaged velocity fields are obtained at the center of the mirror for three scenarios: (a) reference case lacking any control elements, (b) guide vane only, and (c) combination of the guide vane and the AC-DBD plasma actuator. The comparison of cases demonstrates that at 25 m/s windward conditions (-5deg) the guide vane is capable of recovering 17% momentum with respect to the reference case. No significant change is observed by activating the AC-DBD plasma actuator. In contrast, at leeward conditions (5deg), the guide vane results in a −20% momentum loss that is rectified to a 6% recovery with actuation. The above implies that for a truck with two mirrors, 23% of momentum may be recovered.

scholarly journals Flow separation control on swept wing with nanosecond pulse driven DBD plasma actuators

2015 ◽  
Vol 28 (2) ◽  
pp. 368-376 ◽  
Author(s):  
Guangyin Zhao ◽  
Yinghong Li ◽  
Hua Liang ◽  
Menghu Han ◽  
Yun Wu
Keyword(s):  
Flow Separation ◽  
Nanosecond Pulse ◽  
Plasma Actuators ◽  
Separation Control ◽  
Swept Wing ◽  
Dbd Plasma ◽  
Flow Separation Control

Leading-Edge Separation Control by Means of Pulsed Vortex Generator Jets

AIAA Journal ◽  
2008 ◽  
Vol 46 (4) ◽  
pp. 837-846 ◽  
Author(s):  
Peter Scholz ◽  
Marcus Casper ◽  
Jens Ortmanns ◽  
Christian J. Kähler ◽  
Rolf Radespiel
Keyword(s):  
Vortex Generator ◽  
Leading Edge ◽  
Separation Control ◽  
Vortex Generator Jets ◽  
Edge Separation

Leading Edge Separation Control by Means of Pulsed Jet Actuators

2006 ◽  
Author(s):  
Peter Scholz ◽  
Jens Ortmanns ◽  
Christian Kahler ◽  
Rolf Radespiel
Keyword(s):  
Leading Edge ◽  
Separation Control ◽  
Pulsed Jet ◽  
Jet Actuators ◽  
Edge Separation
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