Modified Empirical Model of Surface Dielectric Barrier Discharge Plasma Actuator in Flow Control

Fu, Yunhao; Lyu, Yongxi; Shi, Jingping; Wang, Xiaoguang

doi:10.1061/(asce)as.1943-5525.0001474

Cited by 3 publications

(8 citation statements)

References 35 publications

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“…A semiempirical thrust model has been developed by Yoon and Han [27] that takes into account most of the parameters that affect the thrust. Fu et al [28,29] presented a semiempirical model for the SDBD actuator by considering six main parameters affecting the actuator thrust. These parameters include voltage amplitude, frequency, exposed electrode thickness, encapsulated electrode width, relative permittivity, and dielectric thickness.…”

Section: Innovations and Contributionsmentioning

confidence: 99%

“…According to previous studies [28,51,52], body force can be described by a function in the form of ze −z . By considering the distribution function in two dimensions, the body force field can be calculated by…”

Section: Sdbd Plasma Actuator Thrust and Body Force Modelmentioning

confidence: 99%

“…The parameters of the DBD plasma actuator have an evident effect on the plasma region's parameters. Fu et al [28] presume that the plasma region parameters are proportional to tan −1 (a 1 ω 2 ). The decay rates can be approximated according to α x = 0.149 tan −1 (0.1ω 2 ) + 0.485 and α y = −1.099 tan −1 (0.1ω 2 ) + 3.110, respectively [28].…”

Section: Sdbd Plasma Actuator Thrust and Body Force Modelmentioning

confidence: 99%

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Analytical input-output modelling of surface dielectric barrier discharge plasma actuator

Nesaeian,

Homaeinezhad

2023

J. Phys. D: Appl. Phys.

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Surface dielectric barrier discharge (SDBD) actuators are a type of asymmetric dielectric barrier discharge (DBD) actuator that can be used to generate ions and produce thrust for near-space vehicles. In this paper, a physics-based model for SDBD produced thrust is developed that accounts for geometric and environmental variation between SDBDs. The presented SDBD analytical model (SDBD-AM) is based on models for parallel-plate DBDs but accounts for the "virtual electrode" resulting from changing plasma length that is particular to SDBDs. To validate the model, thrust measurements from twelve different configurations from previous studies were used, and the mean absolute percentage error (MAPE) between each configuration and SDBD-AM was determined. The observed effects on the model were attributed to structural effects including electrode width, electrode spacing, dielectric, and environmental effects including pressure, and the apparent uncertainties are different for each effect. As a result, it was obtained that the MAPE between SDBD-AM and the experimental data for different structures is 11%, and for different pressures, it is 12%. The body force field has been simulated using SDBD-AM and a distribution function in COMSOL software, and the body force profile near the exposed electrode has been validated with a previous numerical model. This model can be used for the design and optimization of SDBD actuators and also in the design of control systems such as spacecraft attitude control in order to increase the accuracy and performance of the controller.

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Section: Innovations and Contributionsmentioning

confidence: 99%

Section: Sdbd Plasma Actuator Thrust and Body Force Modelmentioning

confidence: 99%

Section: Sdbd Plasma Actuator Thrust and Body Force Modelmentioning

confidence: 99%

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Analytical input-output modelling of surface dielectric barrier discharge plasma actuator

Nesaeian,

Homaeinezhad

2023

J. Phys. D: Appl. Phys.

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“…Yoon and Han [35] developed a semi-empirical model that treated the plasma actuator as a capacitor in the alternating current (AC) circuit and incorporated some other empirical formulas. Fu et al [36] have gone a step further. They synthesized the experimental data from several pieces of research and proposed a purely empirical model that captured the variation of the body force with the most parameters of the DBD plasma actuator.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation of virtual control surfaces for lift control on NACA0015 airfoil

Fu,

Lyu,

Shi

2023

Phys. Scr.

Self Cite

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The plasma actuators as virtual control surfaces are assessed numerically as a means to control the lift of NACA0015 airfoil at the full angle of attack (without stall). The virtual control surface for increasing lift is realized by the pressure side (PS) plasma actuators that induce an upstream jet and the suction side (SS) plasma actuators that induce a downstream jet (SSD plasma actuator), while the one for reducing lift is realized by the SS plasma actuators that induce an upstream jet (SSU plasma actuator). Numerical simulation is achieved by solving the two-dimensional Reynolds averaged Navier-Stokes using the finite volume method. The plasma actuator adopts the empirical model proposed by the author before. The simulation of the air flow was performed for the freestream velocity of 20 m/s (Re=$1.03\times 10^6$) and the induced jet momentum coefficient between 0.0846\% and 0.9027\%. The calculation results show that the optimal number of DBD actuators for increasing the lift is related to the angle of attack. The SS flow separation of the high angle of attack greatly reduces the control effect of the PS actuator, which can be eliminated by arranging the actuators in front of the separation point. Finally, a virtual control surfaces configuration containing three groups of seven plasma actuators is obtained.

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“…Furthermore, Maden et al [28] converted PIV-based force fields into an empirical model, in order to allow a more straight forward implementation of the experimentally derived PA force in CFD. Likewise, further (semi-)empirical models have been proposed to predict the force distributions under absence of spatially resolved velocity information, but by means of various discharge-specific quantities [29][30][31][32].…”

Section: Introductionmentioning

confidence: 99%

On the interplay of body-force distributions and flow speed for dielectric-barrier discharge plasma actuators

Hehner

Coutinho

Pereira

et al. 2023

J. Phys. D: Appl. Phys.

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The dielectric-barrier discharge plasma actuator is a well-established device commonly operated in boundary-layer airflows for active flow control. In the present experimental investigation, their ability to cause momentum transfer to the surrounding fluid is analyzed by means of spatio-temporal body-force distributions in both quiescent air and external airflow conditions. The work is motivated by the limitation to quiescent-air operating conditions of frequent previous efforts. Available analytical velocity-information-based force derivation approaches are contrasted to investigate the actuator performance under conditions of their area of application. Results of body force in quiescent air, in agreement with literature, confirm the major taken assumption for Navier-Stokes-based body-force formulations -- a negligible pressure gradient. However, the previous circumstance turns out as an invalid assumption for plasma actuation encountering an external airflow. These outcomes coincide with the findings in the numerical work of [``Numerical investigation of plasma-actuator force-term estimations from flow experiments'', J. Phys. D: Appl. Phys. 48 395203 (2015)], following the recommendation to apply a vorticity-equation-based approach under such conditions. Furthermore, the shape of the spatio-temporal body-force distribution is observed to undergo changes when the airflow speed increases. On the other hand, the integral forcemagnitude is found to remain approximately constant. Moreover, the choice of phase resolution of the discharge cycle has an implication on the accuracy of the temporal force evolution, therefore, clarifying the importance of a priori defining the type of body-force analysis in an experiment; i.e. integral force magnitude, time-averaged or time-resolved evaluation. As a promising finding of utmost importance for the actuator performance, the actuator remains as effective as in quiescent air under presence of the external airflow, which immediately renders the actuator fluid-mechanic efficiency to increase for increasing airflow speed.

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Modified Empirical Model of Surface Dielectric Barrier Discharge Plasma Actuator in Flow Control

Cited by 3 publications

References 35 publications

Analytical input-output modelling of surface dielectric barrier discharge plasma actuator

Analytical input-output modelling of surface dielectric barrier discharge plasma actuator

Numerical investigation of virtual control surfaces for lift control on NACA0015 airfoil

On the interplay of body-force distributions and flow speed for dielectric-barrier discharge plasma actuators

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