Aerodynamic modification of flow over bluff objects by plasma actuation

Sung, Yongjin; Kim, W.; Mungal, M. G.; Cappelli, Mark A.

doi:10.1007/s00348-006-0175-0

Cited by 80 publications

(46 citation statements)

References 14 publications

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“…It should be noted that compared to the EHD effect, the effect of Joule heating in surface DBD actuators driven by AC voltage waveforms appears insignificant. [17][18][19] This paper describes the development and application of nanosecond pulse driven DBD plasma actuators for controlling flow separation from an airfoil leading edge. The NS-DBD plasma actuator is characterized using electrical measurements and optical techniques in quiescent air.…”

Section: Report Datementioning

confidence: 99%

Separation Control with Nanosecond-Pulse-Driven Dielectric Barrier Discharge Plasma Actuators

et al. 2012

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Section: Report Datementioning

confidence: 99%

Separation Control with Nanosecond-Pulse-Driven Dielectric Barrier Discharge Plasma Actuators

et al. 2012

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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%

“…In recent review papers, Corke et al 17 and Wang et al, 18 have summarized both the physics and the application of DBD plasma actuators. 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.…”

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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“…This induces a wall jet on the edge of the exposed electrode. As a flow control method, the plasma actuators have been studied on various aerodynamic research objects in wind tunnel, such as airfoil, [14][15][16] wing, [17][18][19][20] cylinder, [21][22][23][24] turbines blade, 25 and compressor cascade.…”

Section: Introductionmentioning

confidence: 99%

Coherent structures induced by dielectric barrier discharge plasma actuator

Zhang

Choi

et al. 2017

Mod. Phys. Lett. B

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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 f 0 = 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.

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Aerodynamic modification of flow over bluff objects by plasma actuation

Cited by 80 publications

References 14 publications

Separation Control with Nanosecond-Pulse-Driven Dielectric Barrier Discharge Plasma Actuators

Separation Control with Nanosecond-Pulse-Driven Dielectric Barrier Discharge Plasma Actuators

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

Coherent structures induced by dielectric barrier discharge plasma actuator

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