Computational and experimental analysis of flow structures induced by a plasma actuator with burst modulations in quiescent air

Aono, Hikaru; Sekimoto, Satoshi; Sato, Makoto; Yakeno, Aiko; Nonomura, Taku; Fujii, Kozo

doi:10.1299/mej.15-00233

Cited by 35 publications

(43 citation statements)

References 43 publications

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“…In this equation, Q c;ref and E ref were set as the maximum values of Q c and E in the precomputation of the Suzen model. The induced flow in a quiescent field through the computation with the Suzen model has been confirmed using the experimental data for steady [36] and unsteady actuation cases [42]. For the unsteady actuation case especially, the distribution of the induced flow by the Suzen model well predicted the experimental results when the excitation strength (D c ) was set to the appropriate range [42].…”

Section: B Modeling Of the Plasma Actuatorsupporting

confidence: 56%

“…The induced flow in a quiescent field through the computation with the Suzen model has been confirmed using the experimental data for steady [36] and unsteady actuation cases [42]. For the unsteady actuation case especially, the distribution of the induced flow by the Suzen model well predicted the experimental results when the excitation strength (D c ) was set to the appropriate range [42]. To get the appropriate D c value, we conducted many precomputations on the induced flowfield from the plasma actuator in a quiescent field using the distribution in Fig.…”

Section: B Modeling Of the Plasma Actuatormentioning

confidence: 59%

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Multifactorial Effects of Operating Conditions of Dielectric-Barrier-Discharge Plasma Actuator on Laminar-Separated-Flow Control

et al. 2015

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A substantial number of large-eddy simulations are conducted on separated flow controlled by a dielectric barrier discharge plasma actuator at a Reynolds number of 63,000. In the present paper, the separated flow over a NACA 0015 airfoil at an angle of attack of 12 deg, which is just poststall, is used as the base flow for separation control. The effects of the location and operating conditions of the plasma actuator on the separation control are investigated by a parametric study. The control effect is evaluated based on the improvement of not only the lift coefficient but also the drag coefficient over an airfoil. The most effective location of the plasma actuator for both lift and drag improvement is precisely confirmed to be upstream of the natural separation point. Even a low burst ratio is found to be sufficient to obtain the same improvements as the cases with a high burst ratio. The effective nondimensional burst frequency F is observed at 4 ≤ F ≤ 6 for the improvement in the lift coefficient and at 6 ≤ F ≤ 20 for that in the drag coefficient.The lift/drag ratio shows a clear peak at 6 ≤ F ≤ 10. To clarify the mechanism of the laminar-separation control, the effect of a turbulent transition is investigated. There is a clear relationship between the separation control effect and the turbulent transition at the shear layer. An earlier and smoother transition case shows greater improvements in the lift and drag coefficients. Flow analyses show that the cases with early and smooth turbulent transition can attach the separated flow further upstream, resulting in a higher suction peak of the pressure coefficient. In addition, another mechanism of the separation control is observed in which the lift coefficient is improved, not by the reattachment through the turbulent transition but by the large-scale vortex shedding induced by the actuation. It is possible to separate these two dominant mechanisms based on the effect of the turbulent transition on the separation control. Nomenclature a = speed of sound BR = burst ratio C D = drag coefficientlength scale D c = ratio between electrostatic body force added by plasma actuator and dynamic pressure D c;effe = effective D c value E i = electric field vector induced by plasma actuator e = total energy per unit volume F base = nondimensional base frequency for sine wave of input voltage; f base c∕u ∞ F = nondimensional frequency of burst wave; f c∕u ∞ f = frequency f base = base frequency for sine wave of input voltage f = frequency of burst wave M ∞ = freestream Mach number Pr = Prandtl number p = pressure Q c = electric charge q i = heat flux vector Re = Reynolds number St = Strouhal number S Suzen = body force vector determined from Suzen model S i = body force vector; Q c E i T = burst wave period T base = period of sine wave T off = period when sine wave switch is off during burst wave period T on = period when sine wave switch is on during burst wave period t = time u = velocity in chord direction . Member AIAA. Article in Advance / 1 AIAA JOURNAL Downloaded by U...

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Section: B Modeling Of the Plasma Actuatorsupporting

confidence: 56%

Section: B Modeling Of the Plasma Actuatormentioning

confidence: 59%

Multifactorial Effects of Operating Conditions of Dielectric-Barrier-Discharge Plasma Actuator on Laminar-Separated-Flow Control

et al. 2015

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“…Recent investigations have been made at reproducing the non-stationary character of the produced flow while using a modified Suzen & Huang model that is originally time-independent. In these studies (20,21,22), the Suzen & Huang model is modulated by a sinusoidal wave in order to reproduce the influence of the driving AC frequency but the model is also further modulated in burst mode in order to achieve low-frequency periodic perturbations as performed in experiments. This advanced modelling has been validated for quiescent fluid conditions by a comparison with experiments in 20 but the method has also been implemented for manipulating a stalled NACA0015 aerofoil (21,22) and the obtained numerical results confirm that the lift and drag coefficients can been significantly improved by using burst mode actuation.…”

Section: Introductionmentioning

confidence: 99%

Modelling of Dielectric Barrier Discharge Plasma Actuators for Direct Numerical Simulations

Brauner

Laizet

Bénard

et al. 2016

8th AIAA Flow Control Conference

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In recent years the development of devices known as plasma actuators has advanced the promise of controlling flows in new ways that increase lift, reduce drag and improve aerodynamic efficiencies; advances that may lead to safer, more efficient and quieter aircraft. The large number of parameters (location of the actuator, orientation, size, relative placement of the embedded and exposed electrodes, materials, applied voltage, frequency) affecting the performance of plasma actuators makes their development, testing and optimisation a very complicated task. Several approaches have been proposed for developing numerical models for plasma actuators. The discharge can be modelled by physics-based kinetic methods based on first principles, by semi-empirical phenomenological approaches and by PIV-based methods where the discharge is replaced by a steady-state body force. The latter approach receives a recent interest for its easy implementation in RANS and U-RANS solvers. Here, a forcing term extracted from experiments is implemented into our high-order Navier-Stokes solver (DNS) in order to evaluate its robustness and ability to mimic the effects of a surface dielectric barrier discharge. This experimental forcing term is compared to the numerical forcing term developed by Suzen & Huang (1, 2) with an emphasis on the importance of the wall-normal component of each model.

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“…Interesting review articles on this subject are presented with some detailed review and analysis of the numerical modeling and analysis studies carried out in the field of EHD flows for DBD actuators. Experimental analysis, visualization of DBD generated flow with smoke, and some very interesting experimental schlieren analysis have also been carried out . Experimental studies and analysis of DBD actuators were carried out to measure the discharge current, the power and the thrust generated by the DBD actuators.…”

Section: Introductionmentioning

confidence: 99%

“…Experimental analysis, [30][31][32] visualization of DBD generated flow 31 with smoke, and some very interesting experimental schlieren analysis have also been carried out. 23,33 Experimental studies [34][35][36][37][38] and analysis of DBD actuators were carried out to measure the discharge current, the power and the thrust generated by the DBD actuators. In a recent experimental study of DBD thermal characteristics 39 under external flow influence, the temperature distribution on the surface of the DBD actuator was analyzed for different dielectric material, applied voltage, and dielectric material thicknesses.…”

mentioning

confidence: 99%

A plasma‐fluid model for EHD flow in DBD actuators and experimental validation

Mushyam

Rodrigues

Páscoa

2019

Numerical Methods in Fluids

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Summary A numerical method to simulate plasma induced electrohydrodynamic flow is proposed in this study. The numerical model consists of three components. Firstly, a potential module to simulate temporal potential and electric field generated in the ionized fluid. Secondly, a plasma module to simulate plasma development and charge particle densities. Finally, a fluid module to simulate the flow affected by the body forces induced by the movement of the charged particles. Fluid flow is modeled using modified predictor‐corrector strategy as proposed in the marker and cell method. The velocity field was corrected to achieve incompressible flow by calculating pressure correction factors, considered in all cells. Numerical convergence and time sensitivity analysis were carried to confirm grid independence and determine an efficient time step for simulations. Numerical computations are validated by comparing with experimental results of discharge currents and current densities. They were found to be in very good agreement thus providing an extensive validation. Furthermore, quiescent flow over a dielectric barrier discharge actuator is simulated in the this study, using the proposed plasma‐fluid model, to model flow evolution and resolve temporal flow features for detailed analysis. The streamline and vorticity plots were analyzed and compared with experimental results, and flow results were found to be in‐line with the experiments.

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Computational and experimental analysis of flow structures induced by a plasma actuator with burst modulations in quiescent air

Cited by 35 publications

References 43 publications

Multifactorial Effects of Operating Conditions of Dielectric-Barrier-Discharge Plasma Actuator on Laminar-Separated-Flow Control

Multifactorial Effects of Operating Conditions of Dielectric-Barrier-Discharge Plasma Actuator on Laminar-Separated-Flow Control

Modelling of Dielectric Barrier Discharge Plasma Actuators for Direct Numerical Simulations

A plasma‐fluid model for EHD flow in DBD actuators and experimental validation

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