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Serpentine geometry plasma actuators for flow control
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10.1063/1.4818622
/content/aip/journal/jap/114/8/10.1063/1.4818622
http://aip.metastore.ingenta.com/content/aip/journal/jap/114/8/10.1063/1.4818622

Figures

Image of FIG. 1.
FIG. 1.

(a) Schematic of DBD plasma actuator and the generated body force. (b) Linear, (c) arc, (d) rectangle, (e) comb/finger, and (f) triangle geometry serpentine actuators.

Image of FIG. 2.
FIG. 2.

(a) Mesh, (b) two-dimensional slice of the body force (at  = 0), and (c) top view of the geometry used to simulate the serpentine geometry plasma actuation. Every other point is shown. The black lines in (b) and (c) refer to where the body force is 1% of the maximum body force.

Image of FIG. 3.
FIG. 3.

(a) Velocity profiles at a location downstream of the plasma actuation for various values of under quiescent conditions. (b) Values of used to calibrate .

Image of FIG. 4.
FIG. 4.

Velocity fields at the ((a) and (c)) pinch point ( = 0), ((b) and (d)) spreading point ( = 0.05) of the serpentine geometry actuator operated under quiescent conditions for ((a) and (b)) simulations with a prescribed induced velocity of and ((c) and (d)) experiments performed by Durcher and Roy. The experimental results have been non-dimensionalized so that the relative sizes of the actuators match.

Image of FIG. 5.
FIG. 5.

Streamlines in the flow fields from the (a) simulation of a serpentine actuator and (b) experiments for a curved serpentine actuator. A black line is used to indicate the location of the actuator. Experimental data from Durscher and Roy.

Image of FIG. 6.
FIG. 6.

Streamwise vorticity at  = 1.025 of the serpentine geometry actuator operated under quiescent conditions for simulation with a prescribed induced velocity of .

Image of FIG. 7.
FIG. 7.

Comparisons of the velocity field near the plasma actuator for the velocity ratio in a boundary layer flow. The (a) pinching and (b) spreading points are shown, along with the (c) streamwise vorticity at  = 1.025. Note that the x and y scales are not equal in (a) and (b).

Image of FIG. 8.
FIG. 8.

(a) Streamtraces (with a background of the u velocity at  = 1.5) and (b) Q-criteria (colored by velocity magnitude) for the case of in a boundary layer flow. The data set is repeated twice more in the z-direction, only a single wavelength was simulated.

Image of FIG. 9.
FIG. 9.

Angle of the vectored jet as the velocity ratio is varied. This angle was measured as the maximum flow angle at the height of downstream of the pinching point.

Image of FIG. 10.
FIG. 10.

Streamwise variations in the (a) velocity magnitudes and (b) streamwise vorticity at  = 1.2 for the case of . The 99% boundary layer height ( ) is marked by the thick solid line.

Image of FIG. 11.
FIG. 11.

Normalized boundary layer streak profiles based on the standard deviation of the streamwise velocity across the span of the boundary layer for (a) , (b) , (c) , and (d) .

Image of FIG. 12.
FIG. 12.

Normalized boundary layer streak (a) velocity magnitude and (b) streamwise vortex magnitude.

Image of FIG. 13.
FIG. 13.

Grid used to perform simulations around an SD7003 airfoil. Every fourth grid point is shown.

Image of FIG. 14.
FIG. 14.

(a) Instantaneous velocity magnitude and (b) streamlines of the baseline separated flow. (c) Power spectral densities of the turbulent kinetic energy for the baseline separated flow at the mid chord and near the trailing edge. (d) Turbulent kinetic energy along the surface of the airfoil for varying .

Image of FIG. 15.
FIG. 15.

Kinetic energy contained in Fourier modes across a number of temporal and spatial frequencies for the baseline separated flow. (a)  = 5.0 and (b)  = 10.0 effects are shown. Separation and reattachment points are marked.

Image of FIG. 16.
FIG. 16.

Duty cycle applied to the plasma body force over a cycle of forcing.

Image of FIG. 17.
FIG. 17.

Geometries of the actuators tested. (a) Linear. (b) Quarter serpentine. (c) Half serpentine. (d) Full serpentine.

Image of FIG. 18.
FIG. 18.

(a) Instantaneous velocity magnitude and ((b) and (c)) Q = 100 iso-surfaces (colored by the velocity magnitude) for the linear geometry actuation as viewed from the (b) top and (c) iso-metric perspectives.

Image of FIG. 19.
FIG. 19.

(a) Power spectral densities of the turbulent kinetic energy and (b) magnitudes of the fundamental frequency (St = 5.0) modes across a number spatial frequencies for the flow actuated by the linear actuator.

Image of FIG. 20.
FIG. 20.

((a) and (d)) Instantaneous velocity magnitude and vortical structures as viewed from the ((b) and (e)) top and ((c) and (f)) iso-metric perspectives. The vortical structures are visualized through the Q-criterion, Q = 100, and colored by the velocity magnitude for the ((a)-(c)) quarter and ((d)-(f)) full serpentine geometries.

Image of FIG. 21.
FIG. 21.

Magnitude of the fundamental frequency (St = 5.0) modes across a number spatial frequencies for the quarter serpentine geometry.

Image of FIG. 22.
FIG. 22.

Magnitude of the (a) spanwise constant (0,1) and (b) fundamental spatial (1,1) Fourier modes at the fundamental temporal frequency.

Image of FIG. 23.
FIG. 23.

Exponential growth rates of Fourier modes for (a) spanwise constant (0,1) and (b) fundamental spatial (1,1) Fourier modes at the fundamental temporal frequency.

Tables

Generic image for table
Table I.

Dimensional and non-dimensional values used to compute the base flow.

Generic image for table
Table II.

Details of the plasma actuator geometries.

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/content/aip/journal/jap/114/8/10.1063/1.4818622
2013-08-23
2014-04-24
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752b84549af89a08dbdd7fdb8b9568b5 journal.articlezxybnytfddd
Scitation: Serpentine geometry plasma actuators for flow control
http://aip.metastore.ingenta.com/content/aip/journal/jap/114/8/10.1063/1.4818622
10.1063/1.4818622
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