Parametric study of a plasma actuator at unsteady actuation by measurements of the induced flow velocity for flow control

Taleghani, Arash Shams; Shadaram, Abdollah; Mirzaei, Mehran; Abdolahipour, Soheila

doi:10.1007/s40430-018-1120-x

Cited by 27 publications

(14 citation statements)

References 23 publications

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“…Alternating Current Dielectric Barrier Discharge (AC-DBD) plasma actuators are one of the frequently used plasma actuators classified within nonthermal electrohydrodynamic actuators [14][15][16][17][18]. They are driven with sinusoidal alternating current and induce ionic wind as a wall jet near the plasma-produced region and thus can add momentum to the boundary layer.…”

Section: Introductionmentioning

confidence: 99%

“…They are driven with sinusoidal alternating current and induce ionic wind as a wall jet near the plasma-produced region and thus can add momentum to the boundary layer. AC-DBD plasma actuators have been widely used and shown to be effective for the reduction of flow separation at low-speed flow regimes with low Reynolds numbers [17]. Nanosecond DBDs (NS-DBDs) are another type of plasma actuators [19].…”

Section: Introductionmentioning

confidence: 99%

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Investigation on Supersonic Flow Control Using Nanosecond Dielectric Barrier Discharge Plasma Actuators

Shahrbabaki

Bazazzadeh

Khoshkhoo

2021

International Journal of Aerospace Engineering

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In this paper, the effects of streamwise Nanosecond Dielectric Barrier Discharge (NS-DBD) actuators on Shock Wave/Boundary Layer Interaction (SWBLI) are investigated in a Mach 2.5 supersonic flow. In this regard, the numerical investigation of NS-DBD plasma actuator effects on unsteady supersonic flow passing a 14° shock wave generator is performed using simulation of Navier-Stokes equations for 3D-flow, unsteady, compressible, and k ‐ ω SST turbulent model. In order to evaluate plasma discharge capabilities, the effects of plasma discharge length on the flow behavior are studied by investigating the flow friction factor, the region of separation bubble formation, velocity, and temperature distribution fields in the SWBLI region. The numerical results showed that plasma discharge increased the temperature of the discharge region and boundary layer temperature in the vicinity of flow separation and consequently reduced the Mach number in the plasma discharge region. Plasma excitation to the separation bubbles shifted the separation region to the upstream around 6 mm, increased SWBLI height, and increased the angle of the separation shock wave. Besides, the investigations on the variations of pressure recovery coefficient illustrated that plasma discharge to the separation bubbles had no impressive effect and decreased pressure recovery coefficient. The numerical results showed that although the NS-DBD plasma actuator was not effective in reducing the separation area in SWBLI, they were capable of shifting the separation shock position upstream. This feature can be used to modify the structure of the shock wave in supersonic intakes in off-design conditions.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Investigation on Supersonic Flow Control Using Nanosecond Dielectric Barrier Discharge Plasma Actuators

Shahrbabaki

Bazazzadeh

Khoshkhoo

2021

International Journal of Aerospace Engineering

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“…Although several active flow control techniques have been explored over the past decades [14][15][16][17], trailing-edge flaps (TEFs) are still one of the most promising devices in the aerial applications or wind turbine industry due to its cost-effectiveness and viability [18,19]. The application of a TEF as an active control technique in unsteady aerodynamics is inspired by the conventional application of the rigid and discrete flaps installed at the trailing edge of aircraft wings or helicopter blades.…”

Section: Introductionmentioning

confidence: 99%

The influence of oscillating trailing-edge flap on the dynamic stall control of a pitching wind turbine airfoil

Seyednia

Masdari

Vakilipour

2019

J Braz. Soc. Mech. Sci. Eng.

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Unsteady operating environment of a horizontal axis wind turbine can induce excessive loads on the blades, originating from rapid variations in angle of attack and consequently dynamic stall (DS) occurrence. Therefore, it is of utmost importance to control the flow around a blade by which fatigue damage is likely to happen. Using two-dimensional incompressible unsteady Reynolds-averaged Navier-Stokes equations in OpenFOAM package, a series of simulations are carried out to assess the viability of an oscillating deformable trailing-edge flap (DTEF) in load and DS control on a pitching wind turbine airfoil which experiences deep DS at Re = 420,000. Results reveal whether or not the airfoil is equipped with an oscillating DTEF, DS vortex forms at high angles of attack. The size, strength and traveling of the DS vortex, however, can be influenced by out-of-phase deflection of the DTEF. More effectively, the change in the airfoil camber line during flap oscillation can remarkably affect the pressure distribution around the airfoil, and hence, significant load alleviation and mean lift enhancement are achievable, all of which help the wind turbine performance and enhance the life span of the components. Moreover, a parametric study on flap size and amplitude of deflection together with a comparison between a discrete flap and a DTEF suggests an out-of-phase oscillation of a large gently curved DTEF, up to 30% of the total chord, with similar amplitude and frequency with respect to the airfoil is the best condition under which fatigue load control as well as enhancement in resultant load for a blade rotation can take place.

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“…The charged particles are then driven by electric force, thereby forming an air stream between the corona and the collector electrodes. Wind-driven devices based on the ionic wind principle, also called electrostatic air accelerators, have shown vast potential in the fields of flow control [1,2], electronic cooling [3,4], air drying [5,6], and enhanced combustion [7,8] due to advantages of low-energy consumption, use of nonmovable components, compact structure, and flexible design [9,10].…”

Section: Introductionmentioning

confidence: 99%

Parametric Study and Optimization of Flow Characteristics of Wire-Nonparallel Plate-Type Electrostatic Air Accelerators

Zhang

Wang

et al. 2018

Journal of Fluids Engineering

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Wire and nonparallel plate electrode-type electrostatic air accelerators have attracted significant interest. The physical process involved in using accelerators is complicated. Moreover, mechanisms are unclear, especially for accelerators with double- and multiwire electrodes. In this study, the two-dimensional (2D) model of a wire-nonparallel plate-type accelerator validated by experiments is established with a finite element method. Onset voltage, average current, and outlet average velocity are analyzed with respect to different parameters. Onset voltage is derived by the proposed quadratic regression extrapolation method. Moreover, current is affected by interference and discharge effects, while velocity is also influenced by the suction effect. For the single-wire electrode, high wind speed can be obtained by either increasing channel slope or placing the wire near the entry section. For the double-wire electrode, velocity can be further increased when one of the wires is placed near the inlet and the distance between the two wires is widened. Comparatively, the velocity of the three-wire electrode is higher with larger gaps between wires and stronger discharge effect. The highest velocity is obtained by the four-wire electrode. Comparisons indicate that higher velocity can be obtained with weaker interference effect, stronger suction effect, and intensified discharge effect. Optimum parameter combinations are considered by the Taguchi method. Consequently, velocity can be enhanced by more than 39% after optimization compared with the reference design.

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Parametric study of a plasma actuator at unsteady actuation by measurements of the induced flow velocity for flow control

Cited by 27 publications

References 23 publications

Investigation on Supersonic Flow Control Using Nanosecond Dielectric Barrier Discharge Plasma Actuators

Investigation on Supersonic Flow Control Using Nanosecond Dielectric Barrier Discharge Plasma Actuators

The influence of oscillating trailing-edge flap on the dynamic stall control of a pitching wind turbine airfoil

Parametric Study and Optimization of Flow Characteristics of Wire-Nonparallel Plate-Type Electrostatic Air Accelerators

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