Circular cylinder drag reduction by three-electrode plasma actuators

Sosa, Roberto; D’Adamo, Juan; Artana, Guillermo

doi:10.1088/1742-6596/166/1/012015

Cited by 22 publications

(21 citation statements)

References 24 publications

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“…Sosa et al used a three-electrode DBD actuator on a cylinder surface and achieved drag reduction of 25% with respect to the base flow configuration. 20 The electrodes could be configured such that the net force due to ion drift was in the streamwise direction leading to suppression of flow separation. Thomas et al 21 and Kozlov and Thomas 22 implemented DBD plasma actuation for flow control on a circular cylinder at Reynolds numbers as high as 85,000.…”

Section: Active Forcing With Dbd Plasma Actuatorsmentioning

confidence: 99%

Effect of Three-Dimensional Plasma Actuation on the Wake of a Circular Cylinder

Bhattacharya

Gregory

2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Dielectric-barrier discharge plasma actuators were mounted on a circular cylinder in a square wave pattern for active forcing of the cylinder wake. The intermittent spacing of the buried electrodes created a spanwise modulated blowing profile, such that three-dimensional instabilities in the wake were targeted for control. Two distinct power levels of 5.6 and 13.6 watts were used for forcing the flow. Considerable spanwise variation in the wake was achieved with the lower power forcing when the actuators were mounted at the location of maximum shear layer receptivity. This spanwise variation was a direct consequence of the difference in the vorticity levels of the shed vortices from the cylinder. High power forcing nearly eliminated vortex shedding, leading to considerable amount of drag reduction as measured in the far wake. Nomenclaturewire voltage 2 f = frequency f st = vortex shedding frequency L = length along the actuator (spanwise direction) Re = Reynolds number t = time T s = period of vortex shedding u = fluctuating component of U ũ = periodic component of u u = random component of u U = streamwise velocity component U  = freestream velocity U j = plasma actuator jet velocity U = streamwise velocity component U = mean of streamwise velocity component v = fluctuating component of V V = transverse velocity component V = mean of transverse velocity component x = streamwise direction y = transverse direction z = spanwise direction  = spanwise wavelength of actuator ω z = spanwise vorticity

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Section: Active Forcing With Dbd Plasma Actuatorsmentioning

confidence: 99%

Effect of Three-Dimensional Plasma Actuation on the Wake of a Circular Cylinder

Bhattacharya

Gregory

2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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“…1 3 manipulate the dynamics of different flows, such as separated flows (Corke and Post 2005;Little and Samimy 2010;McLaughlin et al 2006;Kelley et al 2012;Jukes and Choi 2009), developing shear layers (Sosa et al 2009a;Benard et al 2008;Thomas et al 2008) or boundary layer laminar-to-turbulent transitions (Joussot et al 2010;Grundmann and Tropea 2007;Hanson et al 2010). 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).…”

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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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“…It is important to note that this method of flow control is not due to simple delay of separation, as has been done on many other occasions. [19][20][21][22][23] Rather, this flow control scheme employs direct wake control. Destruction of the spanwise coherence is evidenced by the reduced coherence between the hot wire probes positioned downstream of the plasma and no-plasma regions (Bhattacharya and Gregory 2 ), the increased number of vortex dislocations seen in the no-plasma region (Fig.…”

Section: Discussionmentioning

confidence: 99%

“…Sung et al 19 found that the ion wind produced by the plasma actuator delayed the separation location on a cylinder, resulting in reduced momentum deficit. Sosa et al 20 used a three-electrode DBD actuator on a cylinder surface and achieved drag reduction of 25% with respect to the base flow configuration. The electrodes could be configured such that the net force due to ion drift was in the streamwise direction leading to suppression of flow separation.…”

Section: Flow Control Using Plasma Actuatorsmentioning

confidence: 99%

Investigation of the cylinder wake under spanwise periodic forcing with a segmented plasma actuator

Bhattacharya

Gregory

2015

Physics of Fluids

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The wake response to three-dimensional forcing of flow over a circular cylinder was studied. Spanwise-segmented dielectric-barrier discharge plasma actuators were mounted on the cylinder in a square wave pattern for active forcing of the cylinder wake. The buried electrodes were placed periodically to create a spanwise-modulated blowing profile, with the aim of targeting three-dimensional instabilities in the wake. Considerable spanwise variation in the wake was achieved, which was a direct consequence of the difference in the location of shed spanwise vortices from the cylinder, along with the generation of streamwise vorticity. Two distinct power levels were used for forcing the flow, with different flow response observed between the two conditions. With low power, the segmented forcing caused the large-scale spanwise structures in the forcing region to lead those in the no-forcing region, with an accompanying shift away from the centerline and generation of streamwise vorticity. While vortex shedding was not substantially attenuated with low-power forcing, the shedding in the near wake was significantly attenuated with high-power forcing. This attenuation in the shedding strength was accompanied by a decrease in the peak shedding frequency, indicating an increase in the formation length. High-power forcing caused elongation of the Kármán vortices due to the induced strain field and strong differential development of the wake shedding frequency. In both forcing regimes, the wake three-dimensionality increased as shown by the increased width of the spectral peaks.

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Circular cylinder drag reduction by three-electrode plasma actuators

Cited by 22 publications

References 24 publications

Effect of Three-Dimensional Plasma Actuation on the Wake of a Circular Cylinder

Effect of Three-Dimensional Plasma Actuation on the Wake of a Circular Cylinder

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

Investigation of the cylinder wake under spanwise periodic forcing with a segmented plasma actuator

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