Quasi-stationary modeling of the DBD plasma flow control around airfoil

Adamiak, K.

doi:10.1063/5.0019732

Cited by 31 publications

(6 citation statements)

References 45 publications

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“…In [45], a resolution method based on finiteelement formulation and Newton iteration was introduced to solve this set of equations considering a single emitter or a pair of emitters placed in a symmetric way and considered as both ignited. The method can be directly used for situations with a larger number of emitters considered as all ignited, as done for instance in [16,44,[48][49][50][51][52].…”

Section: Drift-diffusion Modeling Of Multiple Ignited Emitter: Multi-...mentioning

confidence: 99%

Multi-inception patterns of emitter array/collector systems in DC corona discharge

Lemetayer¹,

Marion²,

Fabre³

et al. 2022

J. Phys. D: Appl. Phys.

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Multiple emitters systems have been previously used so as to increase charge density in the drift region, many times without producing sensible increment neither in total current nor ionic wind. This contribution focuses on analyzing the detailed physics behind this failure, that is named "multiple emitters un-scalability". It is established that multiple emitters un-scalability is related to the inability of multiple corona discharge inceptions when increasing the emitter number and/or density. This confirms recent findings that corona discharge inception is shielded by electro-static interactions between emitters. This contribution demonstrates that this shielding can be balanced by emitter/collector electrostatic interactions depending on the considered configuration. For sufficiently close collector-emitter distances, ignition starts at the array center, whereas, on the contrary, when the collector is distant, the ignition not only starts at the array's periphery but might also be limited there.It is also demonstrated that emitter/emitter electrostatic interactions can be balanced by emitter/collector ones, depending of their chosen configuration. This lead to a variety of multi-inception patterns, the condition of which are analyzed. Intermediate configurations for which the collector is neither sufficiently close nor distant from the emitter array center provide a variety of multi-inception patterns that are hereby analyzed. Combining finite element computations of multi-inception drift-diffusion modeling with experimental measurements, provides a coherent picture explaining why multiple emitters sources systems do not lead to full ignition, and also exhibit conditions for which it does, leading to multiple emitters scalable systems.

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Section: Drift-diffusion Modeling Of Multiple Ignited Emitter: Multi-...mentioning

confidence: 99%

Multi-inception patterns of emitter array/collector systems in DC corona discharge

Lemetayer¹,

Marion²,

Fabre³

et al. 2022

J. Phys. D: Appl. Phys.

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“…In this way, a body force is imposed to the plasma region, producing a noticeable near-wall jet typically less than 10 m s −1 . This flow phenomenon, frequently termed as the momentum effects of DBD actuators [6], can be leveraged not only to reduce the skin friction drag in turbulent boundary layer [2,[7][8][9], but also to suppress the flow separation of airfoils/wings in low speed (Ma < 0.4) [1,[10][11][12].…”

mentioning

confidence: 99%

Effect of pulse width on the characteristics of a dielectric barrier discharge plasma actuator driven by high-voltage pulses

Su¹,

Zong²,

Liang³

et al. 2021

J. Phys. D: Appl. Phys.

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In this study, high-voltage pulses are used to drive dielectric barrier discharge plasma actuators (DBDAs) for flow control purposes. The rising/falling edges of the pulse are kept nearly constant in nanosecond timescale, while the pulse width is varied from nanosecond to microsecond timescale. The impact of pulse width on the characteristics of the DBDA is investigated experimentally with a high-speed schlieren system and a high-fidelity force balance. In the case of small pulse width, a pressure wave propagating at the local speed of sound is produced each time at discharge ignition, and a vertical jet plume is induced after multiple discharge pulses due to heat accumulation (buoyancy effect). As a comparison, for cases with large pulse widths, two pressure waves are created sequentially with a time lag close to the pulse width, and a starting vortex followed by a near-wall jet is produced, demonstrating that significant momentum similar to that of DBD driven by sinusoidal high voltage has been imparted to the near-wall flow. A proportional increase of the induced body force with the cube root of the pulse width is demonstrated, while the pulse energy decreases nonlinearly as the pulse width increases. The maximum body force of 2.49 mN m−1 is reached at a pulse width of 380 μs.

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“…The boundary of the computational domain is 15c from the airfoil surface and 20c from the trailing edge. The mesh near the leading [48], the Spalart-Allmaras model is selected as the near wall turbulence model, which is also consistent with the selection of Fu et al [36] when simulating single DBD plasma actuator. The pressure based solver is adopted, the pressure velocity coupling method adopts the SIMPLE scheme, and the convection term is solved by a second-order upwind scheme.…”

Section: Airfoil and Meshingmentioning

confidence: 91%

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

Fu,

Lyu,

Shi

2023

Phys. Scr.

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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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Quasi-stationary modeling of the DBD plasma flow control around airfoil

Cited by 31 publications

References 45 publications

Multi-inception patterns of emitter array/collector systems in DC corona discharge

Multi-inception patterns of emitter array/collector systems in DC corona discharge

Effect of pulse width on the characteristics of a dielectric barrier discharge plasma actuator driven by high-voltage pulses

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

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