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

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 Control of leading edge separation on airfoil using DBD plasma actuator

2014 ◽  
Vol 9 (3) ◽  
pp. JFST0049-JFST0049 ◽  
Author(s):  
Nazri MD DAUD ◽  
Yasuaki KOZATO ◽  
Satoshi KIKUCHI ◽  
Shigeki IMAO
Keyword(s):  
Leading Edge ◽  
Plasma Actuator ◽  
Dbd Plasma ◽  
Edge Separation

Control of leading edge separation on airfoil using DBD plasma actuator with signal amplitude modulation

2015 ◽  
Vol 19 (1) ◽  
pp. 37-47 ◽  
Author(s):  
Nazri Md Daud ◽  
Yasuaki Kozato ◽  
Satoshi Kikuchi ◽  
Shigeki Imao
Keyword(s):  
Amplitude Modulation ◽  
Leading Edge ◽  
Signal Amplitude ◽  
Plasma Actuator ◽  
Dbd Plasma ◽  
Edge Separation

Plasma-Actuator Burst-Mode Frequency Effects on Leading-Edge Flow-Separation Control at Reynolds Number 2.6×105

AIAA Journal ◽  
2017 ◽  
Vol 55 (11) ◽  
pp. 3789-3806 ◽  
Author(s):  
Hikaru Aono ◽  
Soshi Kawai ◽  
Taku Nonomura ◽  
Makoto Sato ◽  
Kozo Fujii ◽  
...  
Keyword(s):  
Reynolds Number ◽  
Flow Separation ◽  
Leading Edge ◽  
Plasma Actuator ◽  
Mode Frequency ◽  
Separation Control ◽  
Flow Separation Control ◽  
Frequency Effects ◽  
Burst Mode ◽  
Edge Flow

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

Computational Study of Aerodynamic Characteristics of an Airfoil With DBD Plasma Actuator

2011 ◽  
Author(s):  
Kengo Asada ◽  
Kozo Fujii
Keyword(s):  
Computational Study ◽  
Lift Coefficient ◽  
Leading Edge ◽  
Aerodynamic Characteristics ◽  
Plasma Actuator ◽  
Separation Control ◽  
Vortex Center ◽  
Dbd Plasma ◽  
Burst Frequency ◽  
Burst Mode

The relation between aerodynamic characteristics and the effectiveness of separation control with the DBD plasma actuator over the airfoil are discussed. The flow-fields around the NACA0015 airfoil are simulated with implicit large-eddy simulation using compact difference scheme. The normal mode generates moderately separated region over the airfoil and gains lift by negative pressure at the vortex center. The burst mode with nondimensional burst frequency of 1 enhances the vortex shedding from the separation shear layer and avoid the massive separation from the leading edge. However, the lift coefficient oscillate very much, in this case. The burst mode with nondimensional burst frequency of 6 improves the airfoil performance by suppressing the separation region. These facts indicate that the unsteady aerodynamic characteristics must be discussed when the effectiveness of separation control is evaluated.

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