Effect of Burst Frequency and Reynolds Number on Flow Control Authority of DBD Plasma Actuator on NACA0012 Airfoil

2014 ◽  
Author(s):  
Taufik Sulaiman ◽  
Hikaru Aono ◽  
Satoshi Sekimoto ◽  
Masayuki Anyoji ◽  
Taku Nonomura ◽  
...  
Keyword(s):  
Reynolds Number ◽  
Flow Control ◽  
Plasma Actuator ◽  
Dbd Plasma ◽  
Burst Frequency ◽  
Naca0012 Airfoil ◽  
Control Authority

scholarly journals Dynamic Burst Actuation to Enhance the Flow Control Authority of Plasma Actuators

Aerospace ◽  
2021 ◽  
Vol 8 (12) ◽  
pp. 396
Author(s):  
Takuto Ogawa ◽  
Kengo Asada ◽  
Satoshi Sekimoto ◽  
Tomoaki Tatsukawa ◽  
Kozo Fujii
Keyword(s):  
Flow Control ◽  
Stokes Equations ◽  
Computational Study ◽  
Single Point ◽  
Leading Edge ◽  
Plasma Actuator ◽  
Control Cost ◽  
Dbd Plasma ◽  
Burst Frequency ◽  
Airfoil Surface

A computational study was conducted on flows over an NACA0015 airfoil with dielectric barrier discharge (DBD) plasma. The separated flows were controlled by a DBD plasma actuator installed at the 5% chord position from the leading edge, where operated AC voltage was modulated with the duty cycle not given a priori but dynamically changed based on the flow fluctuations over the airfoil surface. A single-point pressure sensor was installed at the 40% chord position of the airfoil surface and the DBD plasma actuator was activated and deactivated based on the strength of the measured pressure fluctuations. The Reynolds number was set to 63,000 and flows at angles of attack of 12 and 16 degrees were considered. The three-dimensional compressible Navier–Stokes equations including the DBD plasma actuator body force were solved using an implicit large-eddy simulation. Good flow control was observed, and the burst frequency proven to be effective in previous fixed burst frequency studies is automatically realized by this approach. The burst frequency is related to the characteristic pressure fluctuation; our approach was improved based on the findings. This improved approach realizes the effective burst frequency with a lower control cost and is robust to changing the angle of attack.

Computational Study of Wing Tip Effect for the Flow Control Authority of DBD Plasma Actuator

2019 ◽  
Author(s):  
Takumi Abe ◽  
Kengo Asada ◽  
Satoshi Sekimoto ◽  
Koji Fukudome ◽  
Hiroya Mamori ◽  
...  
Keyword(s):  
Flow Control ◽  
Computational Study ◽  
Plasma Actuator ◽  
Dbd Plasma ◽  
Control Authority ◽  
Wing Tip

Comparison of Two Active Flow Control Mechanisms of Pure Blowing and Pure Suction on a Pitching NACA0012 Airfoil at Reynolds Number of 1 × 106

2018 ◽  
Author(s):  
Ehsan Asgari ◽  
Mehran Tadjfar
Keyword(s):  
Reynolds Number ◽  
Flow Control ◽  
Active Flow Control ◽  
Hysteresis Loops ◽  
Leading Edge ◽  
Control Mechanisms ◽  
Airfoil Surface ◽  
Naca0012 Airfoil ◽  
Maximum Angle ◽  
Active Flow

In this study, we have applied and compared two active flow control (AFC) mechanisms on a pitching NACA0012 airfoil at Reynolds number of 1 × 106 using 2-D computational fluid dynamics (CFD). These mechanisms are continuous blowing and suction which are applied separately on the airfoil which pitches around its quarter-chord in a sinusoidal motion. The location for suction and blowing was determined in our previous study based on the formation of a counter clock-wise vortex near the leading-edge. In our current study, we have compared the effectiveness of pure blowing and pure suction in suppressing the dynamic stall vortex (DSV) which is the main contributor to the drag increase, particularly near the maximum angle of attack (AOA) and in early downstroke motion. The blowing/suction slot is considered as a dent on the airfoil surface which enables the AFC to perform in a tangential manner. This configuration would allow blowing jet to penetrate further downstream and was shown to be more effective compared to a cross-flow orientation. We have compared the two aforementioned mechanisms in terms of hysteresis loops of lift and drag coefficients and have demonstrated the dynamics of flow in controlled and uncontrolled situations.

scholarly journals Coherent structures induced by dielectric barrier discharge plasma actuator

2017 ◽  
Vol 31 (32) ◽  
pp. 1850038 ◽  
Author(s):  
Xin Zhang ◽  
Huaxing Li ◽  
Kwing So Choi ◽  
Longfei Song
Keyword(s):  
Flow Control ◽  
Dielectric Barrier Discharge ◽  
Coherent Structures ◽  
High Speed ◽  
Barrier Discharge ◽  
Plasma Actuator ◽  
Dbd Plasma ◽  
Peak Voltage ◽  
Dielectric Barrier ◽  
Piv Measurement

The structures of a flow field induced by a plasma actuator were investigated experimentally in quiescent air using high-speed Particle Image Velocimetry (PIV) technology. The motivation behind was to figure out the flow control mechanism of the plasma technique. A symmetrical Dielectric Barrier Discharge (DBD) plasma actuator was mounted on the suction side of the SC (2)-0714 supercritical airfoil. The results demonstrated that the plasma jet had some coherent structures in the separated shear layer and these structures were linked to a dominant frequency of [Formula: see text] = 39 Hz when the peak-to-peak voltage of plasma actuator was 9.8 kV. The high speed PIV measurement of the induced airflow suggested that the plasma actuator could excite the flow instabilities which lead to production of the roll-up vortex. Analysis of transient results indicated that the roll-up vortices had the process of formation, movement, merging and breakdown. This could promote the entrainment effect of plasma actuator between the outside airflow and boundary layer flow, which is very important for flow control applications.

Sign in / Sign up

Export Citation Format

Share Document