Single Nanosecond Dielectric Barrier Discharge and Pulsed Sliding Discharge Applied to Separation Control Along a NACA 0015 Airfoil

2015 ◽  
Author(s):  
Kossi D. Bayoda ◽  
Nicolas Benard ◽  
Eric Moreau
Keyword(s):  
Dielectric Barrier Discharge ◽  
Barrier Discharge ◽  
Separation Control ◽  
Dielectric Barrier ◽  
Naca 0015 ◽  
Sliding Discharge

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.

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