Abstract
In this study, the separation control of an airfoil when a dielectric barrier discharge (DBD) plasma actuator is mounted on its leading edge was examined. Experiments were performed at a Reynolds number of approximately 67,000 with an external airflow of 10 m/s. The DBD plasma actuator was installed on an NACA 0015 airfoil with a 100 mm chord and 150 mm width at x/c = 0.025, where x was the vertical distance measured from the leading edge and c was the chord length. Lift force measurements, flow visualization and velocity measurements were conducted to investigate the performance of the DBD plasma actuator, which was driven by either pulse modulation with amplitude modulation (PM + AM) or pulse modulation only (PM). The PM + AM case was designed to consume the same amount of power as the PM case. The result showed that the PM + AM case improved the lift coefficient compared to the PM case for both St = 0.6 and St = 4.0. Under the stall control condition (angle of attack, α = 16°) and high angle of attack condition (α = 18°), the PM + AM case always demonstrated improved lift over the PM case; the improvement in lift was greater at α = 18° than at α = 16°. Flow visualization confirmed larger and stronger vortex shedding for the PM + AM case over the PM case.
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Abbreviations
- A :
-
Wing area
- C l :
-
Lift coefficient = L/(0.5\( \rho U_{0}^{2} A \))
- c :
-
Chord length
- Duty:
-
Ratio of ON time to period of modulation actuation (duty ratio) = T on/T
- f B :
-
Base frequency
- f M :
-
Modulation frequency = 1/T
- L :
-
Lift force
- Re :
-
Reynolds number = U 0 c/ν
- St:
-
Non-dimensional pulse modulation frequency = f M c/U 0
- T :
-
Period of ON–OFF cycle
- T on :
-
Period that DBD plasma actuator is ON
- U 0 :
-
Uniform flow velocity
- u′ :
-
Root mean square value of fluctuating velocity
- x, y :
-
Horizontal and vertical distances measured from leading edge
- α :
-
Angle of attack
- \( \rho \) :
-
Air density
- \( \nu \) :
-
Kinematic viscosity of air
References
Amitay M, Glezer A (2002) Role of actuation frequency in controlled flow reattachment over a stalled airfoil. AIAA J 40(2):209–216
Asada K, Ninomiya Y, Oyama A, Fujii K (2009) Airfoil flow experiment on the duty cycle of DBD plasma actuator, AIAA paper 2009-531, 47th AIAA aerospace sciences meeting
Ashpis DE, Laun MC, Griebeler EL (2012) Progress towards accurate measurements of power consumptions of DBD plasma actuators, AIAA paper 2012-0823, 50th AIAA aerospace science meeting
Balcon N, Benard N, Moreau E (2009a) Formation process of the electric wind produced by a plasma actuator. IEEE Trans Dielectr Electr Insul 16(2):463–469
Balcon N, Bernard N, Lagmich Y, Boeuf JP, Touchard G, Moreau E (2009b) Positive and negative sawtooth signals applied to a DBD plasma actuator—influence on the electric wind. J Electrostat 67:140–145
Bernard N, Moreau E (2010) Capabilities of dielectric barrier discharge plasma actuator for multi-frequency excitations. J Phys D Appl Phys 43:145201
Bernard N, Moreau E (2011) On the vortex dynamic of airflow reattachment forced by a single non-thermal plasma discharge actuator. Flow Turbul Combust 87:1–31
Bernard N, Braud P, Jolibois J, Moreau E (2008) Airflow reattachment along a NACA 0015 airfoil by surfaces dielectric barrier discharge actuator—time resolved particle image velocimetry investigation, AIAA paper 2008-4202, 4th flow control conference
Bernard N, Jolibois J, Moreau E (2009) Lift and drag performances of an axisymmetric airfoil controlled by plasma actuator. J Electrostat 67:133–139
Craig H, Rasool E, Konstantinos K (2010) Plasma actuators with multiple encapsulated electrodes to influence the induced velocity, AIAA paper 2010-1223, 43th AIAA aerospace sciences meeting
Forte M, Jolibois J, Pons J, Moreau E, Touchard G, Cazalens M (2007) Optimization of a dielectric barrier discharge actuator by stationary and non-stationary measurements of the induced flow velocity: application to airflow control. Exp Fluids 43:917–928
Jolibois J, Forte M, Moreau E (2008) Application of an AC barrier discharge actuator to control airflow separation above a NACA 0015 airfoil: optimization of the actuation location along the chord. J Electrostat 66:496–503
Jukes TN, Choi KS (2012) Dielectric barrier discharge vortex generators: characterization and optimization for flow separation control. Exp Fluids 52:329–345
Md Daud N, Kozato Y, Kikuchi S, Imao S (2014) Control of leading edge separation on airfoil using DBD plasma actuator. J Fluid Sci Technol 9(3)
Post ML, Corke T (2004) Separation control on high angle of attack airfoil using plasma actuators. AIAA J 42(11):2177–2178
Rethmel C, Little J, Takashima K, Sinha A, Adamovich I, Samimy M (2011) Flow separation control over an airfoil with nanosecond pulse driven DBD plasma actuators, 49th AIAA aerospace sciences meeting
Sosa R, Artana G (2006) Steady control of laminar separation over airfoils with plasma sheet actuators. J Electrostat 64:604–610
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Md Daud, N., Kozato, Y., Kikuchi, S. et al. Control of leading edge separation on airfoil using DBD plasma actuator with signal amplitude modulation. J Vis 19, 37–47 (2016). https://doi.org/10.1007/s12650-015-0283-0
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DOI: https://doi.org/10.1007/s12650-015-0283-0