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

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

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

Flow Separation Control Using Nanosecond Pulse Driven DBD Plasma Actuators

2011 ◽  
Vol 3 (4) ◽  
pp. 213-232 ◽  
Author(s):  
Chris Rethmel ◽  
Jesse Little ◽  
Keisuke Takashima ◽  
Aniruddha Sinha ◽  
Igor Adamovich ◽  
...  
Keyword(s):  
Flow Separation ◽  
Nanosecond Pulse ◽  
Plasma Actuators ◽  
Separation Control ◽  
Dbd Plasma ◽  
Flow Separation Control

Experimental Comparison of DBD Plasma Actuators for Low Reynolds Number Separation Control

2012 ◽  
Vol 135 (1) ◽  
Author(s):  
Christopher R. Marks ◽  
Rolf Sondergaard ◽  
Mitch Wolff ◽  
Rich Anthony
Keyword(s):  
Reynolds Number ◽  
Low Reynolds Number ◽  
Turbine Blades ◽  
Plasma Actuators ◽  
Experimental Comparison ◽  
Separation Control ◽  
Suction Surface ◽  
Dbd Plasma ◽  
Low Reynolds ◽  
Low Reynolds Number Airfoil

This paper presents experimental work comparing several Dielectric Barrier Discharge (DBD) plasma actuator configurations for low Reynolds number separation control. Actuators studied here are being investigated for use in a closed loop separation control system. The plasma actuators were fabricated in the U.S. Air Force Research Laboratory Propulsion Directorate’s thin film laboratory and applied to a low Reynolds number airfoil that exhibits similar suction surface behavior to those observed on Low Pressure (LP) Turbine blades. In addition to typical asymmetric arrangements producing downstream jets, one electrode configurations was designed to produce an array of off axis jets, and one produced a spanwise array of linear vertical jets in order to generate vorticity and improved boundary layer to freestream mixing. The actuators were installed on an airfoil and their performance compared by flow visualization, surface stress sensitive film (S3F), and drag measurements. The experimental data provides a clear picture of the potential utility of each design. Experiments were carried out at four Reynolds numbers, 1.4 × 105, 1.0 × 105, 6.0 × 104, and 5.0 × 104 at a-1.5 deg angle of attack. Data was taken at the AFRL Propulsion Directorate’s Low Speed Wind Tunnel (LSWT) facility.

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