scholarly journals Modeling and Experiment of Leading Edge Separation Control Using SDBD Plasma Actuators

2007 ◽  
Author(s):  
Dmitriy Orlov ◽  
Thomas Apker ◽  
Chuan He ◽  
Hesham Othman ◽  
Thomas Corke
Keyword(s):  
Leading Edge ◽  
Plasma Actuators ◽  
Separation Control ◽  
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

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.

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

Investigation of airfoil leading edge separation control with nanosecond plasma actuator

2016 ◽  
Vol 1 (7) ◽  
Author(s):  
J. G. Zheng ◽  
Y. D. Cui ◽  
Z. J. Zhao ◽  
J. Li ◽  
B. C. Khoo
Keyword(s):  
Leading Edge ◽  
Plasma Actuator ◽  
Separation Control ◽  
Edge Separation

scholarly journals Separation Control of NACA0015 Airfoil using Plasma Actuators

2021 ◽  
Vol 1 (1) ◽  
Author(s):  
Akira Aiura ◽  
Kentaro Kobayashi ◽  
Jun Sakakibara
Keyword(s):  
Separation Bubble ◽  
Leading Edge ◽  
Ccd Camera ◽  
Force Balance ◽  
Plasma Actuators ◽  
Large Field ◽  
Separation Control ◽  
Pressure Transducers ◽  
Periodic Disturbances ◽  
Two Component

Separation control of NACA0015 airfoil using plasma actuators was investigated. Plasma actuators in spanwise array, which consists of 21 electrodes, were located at the leading edge of the airfoil to give temporal periodic disturbances with phase variations into its boundary layer. The cord length of the airfoil was c = 100mm and corresponding Reynolds number was fixed at Re = 63,000. Non-dimensional frequency of the disturbance was chosen at F+ = 0.5 or 6. The gap between adjacent electrode was set as 1mm, and phase difference of the temporal periodic disturbances between adjacent electrode was set at φ = 0 or π. Velocity field was measured by conventional two-component PIV using a CCD camera (Imperx, B1922, 1920 x 1460pixels) and Nd-YAG laser (Quantel, Evergreen, 140mJ/pulse). Both large field of view (FOV) images capturing whole wing with surrounding flow and smaller FOV images focused on the separation bubble near leading edge were evaluated. Surface pressure was monitored by pressure transducers through pressure taps on the upper surface of airfoil. Lift and drag against the airfoil were measured using a two-component force balance.

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