Experimental study on dynamic stall control based on AC-DBD actuation

Yang, Hesen; Liang, Hua; Zhao, Guiping; Wang, Bo; Zhang, Shengwu; Kong, Wei

doi:10.1088/2058-6272/ac1395

Cited by 12 publications

(8 citation statements)

References 41 publications

(59 reference statements)

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The actuator is located at x=141.05 mm, and the metal electrode profile is consistent with the cone. The electrode generates arc plasma actuation through an AC millisecond power supply, and the detailed parameters of the power supply are described in [33]. The PCB sensor and actuator arrangement at the actuation position are displayed in figure 1.…”

Section: Experimental Methods and Designmentioning

confidence: 99%

Experimental study on surface arc plasma actuation-based hypersonic boundary layer transition flow control

Yang¹,

Liang²,

Guo³

et al. 2022

Plasma Sci. Technol.

Self Cite

View full text Add to dashboard Cite

Effective control of hypersonic transition is essential. In order to avoid affecting the structural profile of the aircraft, reduce power consumption and electromagnetic interference, the experiment of low-frequency surface arc plasma disturbance to promote hypersonic transition was carried out in the Φ0.25m double-throat Ludwieg tube wind tunnel of Huazhong University of Science and Technology. The contacting PCB sensors and non-contact focused laser differential interferometry testing technology (FLDI) are used in combination. Experimental results show that the low-frequency surface arc plasma actuation has obvious stimulation effects on the second mode unstable wave and can promote boundary layer transition by changing the spectral characteristics of the second mode unstable wave. At the same time, the plasma actuation can promote the energy exchange between the second mode unstable wave and other unstable waves. Finally, the corresponding control mechanism is discussed preliminarily.

show abstract

Section: Experimental Methods and Designmentioning

confidence: 99%

Experimental study on surface arc plasma actuation-based hypersonic boundary layer transition flow control

Yang¹,

Liang²,

Guo³

et al. 2022

Plasma Sci. Technol.

Self Cite

View full text Add to dashboard Cite

show abstract

“…The upstream of the natural separation point is determined as the optimal location to control the separation flow. Yu et al [38] and Yang et al [39] studied the control ability of the DBD plasma actuator to dynamic stall on an airfoil by numerical and experimental methods, respectively. These studies illustrate the ability of the DBD plasma actuator on the suction side to improve the performance of the airfoil at high angles of attack and even stall.…”

Section: Introductionmentioning

confidence: 99%

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

Fu,

Lyu,

Shi

2023

Phys. Scr.

View full text Add to dashboard Cite

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.

show abstract

“…In addition, for the air jet method, additional cavities inside the airfoil are needed to store the air source, which results in reduction of the rigidity and intensity of the airfoil. In terms of the advantages of the DBD plasma actuation flow control method, including broad frequency response, without moving parts with aerodynamic deformation, and relatively low power consumption, it has been widely applied in lift enhancement [19], boundary-layer control [20], flow separation control [21], noise reduction [22], and turbulent drag reduction [23]. It is worth mentioning that plasma actuators have potential in practical applications in the fields of anti-icing [24] and ice sensing [25,26] in recent studies, which provides favorable conditions for improving the adaptability of wind turbines to complex climates.…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation of dynamic stall flow control using a microsecond-pulsed plasma actuator

Zeyang

Gao

et al. 2023

Plasma Sci. Technol.

View full text Add to dashboard Cite

To alleviate the performance deterioration caused by dynamic stall of the wind turbine airfoil, the flow control by microsecond-pulsed dielectric barrier discharge (MP-DBD) actuator on the dynamic stall of a periodically pitching NACA0012 airfoil was investigated experimentally. The unsteady pressure measurements with high temporal accuracy were employed in this study, and the unsteady characteristics of the boundary layer were investigated by wavelet packet analysis and the moving root mean square (RMS) method based on the acquired pressure. The experimental Mach number was Ma =0.2, and the chord-based Reynolds number was Re = 870000. The dimensionless actuation frequencies F+ were chosen to be 0.5, 1, 2, and 3, respectively. For the light dynamic regime, the MP-DBD plasma actuator plays the role of suppressing flow separation from the trial edge and accelerating the flow reattachment due to the high momentum freestream flow being entrained into the boundary layer. Meanwhile, actuation effects were promoted with the increasing dimensionless actuation frequency F+. The control effects of the deep dynamic stall were to delay the onset and reduce the strength of the dynamic stall vortex (DSV), due to the accumulating vorticity near the leading edge being removed by the induced coherent vortex structures. The laminar fluctuation and K-H (Kelvin-Helmholtz) instabilities of transition and relaminarization were also mitigated by the MP-DBD actuation, and the alleviated K-H rolls lead to the delay of the transition onset and earlier laminar reattachment, which improved the hysteresis effect of the dynamic stall. For the controlled cases of F+ = 2, and F+ = 3, the laminar fluctuation was replaced by relatively low frequency band disturbances corresponding to the harmonic responses of the MP-DBD actuation frequency.

show abstract

Experimental study on dynamic stall control based on AC-DBD actuation

Cited by 12 publications

References 41 publications

Experimental study on surface arc plasma actuation-based hypersonic boundary layer transition flow control

Experimental study on surface arc plasma actuation-based hypersonic boundary layer transition flow control

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

Experimental investigation of dynamic stall flow control using a microsecond-pulsed plasma actuator

Contact Info

Product

Resources

About