Closed-loop Dynamic Stall Control Using a Plasma Actuator

Lombardi, Andrew; Bowles, Patrick; Corke, Thomas

doi:10.2514/6.2012-918

Cited by 18 publications

(10 citation statements)

References 20 publications

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“…Collis et al (2004) have provided an excellent review on active flow control in both open-and closed-loop systems. There are three different methods commonly used to control flow separation: (1) identification of incipient flow separation control method (e.g., Patel et al 2007;Wong and Rinoie 2010;Lombardi et al 2013); (2) linear control theory method (e.g., Kim et al 2006;Kim and Bewley 2007;Huang and Kim 2008); and (3) adaptive control method (e.g., Becker et al 2007;Cho and Shyy 2011). Patel et al (2007) used two feedback control methods to identify incipient flow separation on airfoil: (1) amplitude peak sense and control and (2) pressure amplitude sense and control.…”

Section: Introductionmentioning

confidence: 99%

A rapidly settled closed-loop control for airfoil aerodynamics based on plasma actuation

Wong

Wang

et al. 2015

Exp Fluids

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Section: Introductionmentioning

confidence: 99%

A rapidly settled closed-loop control for airfoil aerodynamics based on plasma actuation

Wong

Wang

et al. 2015

Exp Fluids

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“…Plasma actuators have also been used for flapping airfoil control (Rizzetta & Visbal 2012), airfoil roll control (Wei et al 2013), closed-loop dynamic stall control (Lombardi, Bowles & Corke 2013) as well as suppression of tonal trailing-edge noise from an airfoil (Inasawa, Ninomiya & Asai 2013). Further details on the application of DBD plasma actuators for aerodynamic flow control can be found in recent review papers by Moreau (2007), Corke, Enloe & Wilkinson (2010) and Wang et al (2013).…”

Section: Plasma Flow Controlmentioning

confidence: 99%

Flow control over an airfoil using virtual Gurney flaps

2015

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Flow control over a NACA 0012 airfoil is carried out using a dielectric barrier discharge (DBD) plasma actuator at the Reynolds number of 20 000. Here, the plasma actuator is placed over the pressure (lower) side of the airfoil near the trailing edge, which produces a wall jet against the free stream. This reverse flow creates a quasi-steady recirculation region, reducing the velocity over the pressure side of the airfoil. On the other hand, the air over the suction (upper) side of the airfoil is drawn by the recirculation, increasing its velocity. Measured phase-averaged vorticity and velocity fields also indicate that the recirculation region created by the plasma actuator over the pressure surface modifies the near-wake dynamics. These flow modifications around the airfoil lead to an increase in the lift coefficient, which is similar to the effect of a mechanical Gurney flap. This configuration of DBD plasma actuators, which is investigated for the first time in this study, is therefore called a virtual Gurney flap. The purpose of this investigation is to understand the mechanism of lift enhancement by virtual Gurney flaps by carefully studying the global flow behaviour over the airfoil. First, the recirculation region draws the air from the suction surface around the trailing edge. The upper shear layer then interacts with the opposite-signed shear layer from the pressure surface, creating a stronger vortex shedding from the airfoil. Secondly, the recirculation region created by a DBD plasma actuator over the pressure surface displaces the positive shear layer away from the airfoil, thereby shifting the near-wake region downwards. The virtual Gurney flap also changes the dynamics of laminar separation bubbles and associated vortical structures by accelerating laminar-to-turbulent transition through the Kelvin-Helmholtz instability mechanism. In particular, the separation point and the start of transition are advanced. The reattachment point also moves upstream with plasma control, although it is slightly delayed at a large angle of attack.

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“…In most of these papers, the actuator is used in context of open-loop control, but plasma discharges find a new route in the construction of closed-loop strategies by using DBD (Lombardi et al 2012;Rethmel et al 2011;Grundmann and Tropea 2008;Kriegseis et al 2011a). Instead of manipulating a flow dynamic, the actuator can be used as a generator of predefined perturbations easily tuned by the applied electrical signal (Widmann et al 2012).…”

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confidence: 99%

Electrical and mechanical characteristics of surface AC dielectric barrier discharge plasma actuators applied to airflow control

2014

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Sherman 1998). Then, different groups already having background experiences on corona discharges and their interactions with quiescent or moving flows formed a new highly motivated community that contributes to the dissemination of the advantages and relevancy of non-thermal plasma discharges as an alternative to conventional flow actuators (Moreau 2007;Corke et al. 2009Corke et al. , 2010. Rapidly, the number of publications in journals and conference exponentially grows to finally become a full interdisciplinary research field. The sudden interest for surface dielectric barrier discharge (DBD) energized by AC high voltage for manipulating airflows was initially motivated by the easy implementation of these actuators and a possible retrofitting on existing airfoils. They have the capability to be mounted at the surface of linear or curved objects with a minimal protrusion in the flow. Beside, their location can be changed faster than other active actuators that require a new model for each new position of actuation. The amplitude and frequency of the electrohydrodynamic (EHD) force produced by the surface plasma are directly connected to the driven electrical signal, this being a clear advantage for parametric studies on the sensibility of one flow to well-defined perturbations. Indeed, the EHD force (also referred as EFD force for electro-fluid dynamic) and the resulting produced flow called electric wind or ionic wind are due to electric field that acts on charged species. These charged species are produced by physical phenomena such as ionization, recombination, attachment, detachment and photoionization, which occur at timescale of a few picoseconds (Boeuf et al. 2009a). Subsequently, the produced body force, despite being low-pass filtered by fluid mechanical laws (viscosity, energy exchanges, dissipation) to produce electric wind, has a high bandwidth. Plasma actuators, and more specifically dielectric barrier discharge actuators, have demonstrated their authority to Abstract The present paper is a wide review on AC surface dielectric barrier discharge (DBD) actuators applied to airflow control. Both electrical and mechanical characteristics of surface DBD are presented and discussed. The first half of the present paper gives the last results concerning typical single plate-to-plate surface DBDs supplied by a sine high voltage. The discharge current, the plasma extension and its morphology are firstly analyzed. Then, time-averaged and time-resolved measurements of the produced electrohydrodynamic force and of the resulting electric wind are commented. The second half of the paper concerns a partial list of approaches having demonstrated a significant modification in the discharge behavior and an increasing of its mechanical performances. Typically, single DBDs can produce mean force and electric wind velocity up to 1 mN/W and 7 m/s, respectively. With multi-DBD designs, velocity up to 11 m/s has been measured and force up to 350 mN/m.

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Closed-loop Dynamic Stall Control Using a Plasma Actuator

Cited by 18 publications

References 20 publications

A rapidly settled closed-loop control for airfoil aerodynamics based on plasma actuation

A rapidly settled closed-loop control for airfoil aerodynamics based on plasma actuation

Flow control over an airfoil using virtual Gurney flaps

Electrical and mechanical characteristics of surface AC dielectric barrier discharge plasma actuators applied to airflow control

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