Aerodynamic performance enhancement of a flying wing using nanosecond pulsed DBD plasma actuator

Han, Min−Koo; Li, Jun; Niu, Zhongguo; Liang, Hua; Zhao, Guiping; Hua, Weizhuo

doi:10.1016/j.cja.2015.02.006

Cited by 29 publications

(8 citation statements)

References 18 publications

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“…Over the past decade, there has been a great interest in using non-thermal plasma actuators for active flow control of aerodynamic surfaces [1][2][3][4][5][6][7]. Plasma actuators have the potential to control a fluid system while staying silent, instantaneous, and compact [8][9][10]. Generated through corona discharge or dielectric barrier discharge (DBD), the ions are generated when an applied voltage induces an applied electric field that exceeds the dielectric strength of air or any working fluid.…”

Section: Introductionmentioning

confidence: 99%

Empirical relations for discharge current and momentum injection in dielectric barrier discharge plasma actuators

Tang¹,

Vaddi²,

Mamishev³

et al. 2021

J. Phys. D: Appl. Phys.

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Dielectric barrier discharge (DBD) plasma actuators with an asymmetric, straight edge electrode configuration generate a wall-bounded jet without moving parts. Mechanistic description of the interaction between the Coulombic forces and fluid motion as a function of DBD parameters remains unclear. This paper presents an experimental investigation of DBD actuators, including electrical current associated with microdischarges, plasma volume and the wall jet momentum over a range of alternating current (AC) frequencies (0.5–2 kHz) and peak-to-peak voltages up to 19.5 kV. Discharge current is measured with a high temporal resolution, plasma volume is characterized optically and the momentum induced by the DBD wall jet is computed based on the axial velocities measured downstream of the actuator using a custom-built pitot tube. Discharge current analysis demonstrated asymmetry between the positive and negative semi-cycle; both currents yielded a power–law relationship with empirical fitting coefficients. Plasma length varies linearly and volume quadratically with voltage. Although plasma length reached an asymptotic value at a higher frequency, the plasma volume grows due to the increasing height of the ionization region. In a simple two-dimensional configuration, the DBD wall jet momentum shows near-linear dependency with discharge current in the range of voltages and frequencies considered in this work. The presented empirical model characterizes the DBD wall jet momentum and the discharge current based only on the AC inputs. With the estimation of plasma volume, the model can be applied for determining more realistic boundary conditions in numerical simulations.

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Section: Introductionmentioning

confidence: 99%

Empirical relations for discharge current and momentum injection in dielectric barrier discharge plasma actuators

Tang¹,

Vaddi²,

Mamishev³

et al. 2021

J. Phys. D: Appl. Phys.

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“…These changes create a stronger “ion wind” affecting the air circulation in the boundary layer. The most frequently used frequency during experimental research is from several hundred Hz to several kHz [ 17 , 18 , 19 , 20 ]. The voltage range used during the experimental tests depends on the dielectric [ 21 , 22 ] used and ranges from a few kV to several dozen kV.…”

Section: Introductionmentioning

confidence: 99%

Wind Tunnel Testing of Plasma Actuator with Two Mesh Electrodes to Boundary Layer Control at High Angle of Attack

Gnapowski

Pytka

Jóźwik

et al. 2021

Sensors

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The manuscript presents experimental research carried out on the wing model with the SD 7003 profile. A plasma actuator with DBD (Dielectric Barrier Discharge) discharges was placed on the wing surface to control boundary layer. The experimental tests were carried out in the AeroLab wind tunnel where the forces acting on the wing during the tests were measured. The conducted experimental research concerns the analysis of the phenomena that take place on the surface of the wing with the DBD plasma actuator turned off and on. The plasma actuator used during the experimental tests has a different structure compared to the classic plasma actuator. The commonly tested plasma actuator uses solid/impermeable electrodes, while in the research, the plasma actuator uses a new type of electrodes, two mesh electrodes separated by an impermeable Kapton dielectric. The experimental research was carried out for the angle of attack α = 15° and several air velocities V = 5–15 m/s with a step of 5 m/s for the Reynolds number Re = 87,500–262,500. The critical angle of attack at which the SD 7003 profile has the maximum lift coefficient is about 11°; during the experimental research, the angle was 15°. Despite the high angle of attack, it was possible to increase the lift coefficient. The use of a plasma actuator with two mesh electrodes allowed to increase the lift by 5%, even at a high angle of attack. During experimental research used high voltage power supply for powering the DBD plasma actuator in the voltage range from 7.5 to 15 kV.

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“…Han et al studied the actuation frequency of ns-DBD to improve the aerodynamic performance of the flying wing under different Reynolds numbers. The results show that there is an optimal actuation frequency and it is more effective to delay the breakdown of the leading edge vortex at low frequencies [29]. Yao et al studied the optimal actuation position of the ns-DBD to improve the aerodynamic performance of the flying wing.…”

Section: Introductionmentioning

confidence: 99%

Experimental Study on Plasma Flow Control of Symmetric Flying Wing Based on Two Kinds of Scaling Models

Xie

Liang

Han³

et al. 2019

Symmetry

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The symmetric flying wing has a simple structure and a high lift-to-drag ratio. Due to its complicated surface design, the flow field flowing through its surface is also complex and variable, and the three-dimensional effect is obvious. In order to verify the effect of microsecond pulse plasma flow control on the symmetric flying wing, two different sizes of scaling models were selected. The discharge energy was analyzed, and the force and moment characteristics of the two flying wings and the particle image velocimetry (PIV) results on their surface flow field were compared to obtain the following conclusions. The microsecond pulse surface dielectric barrier discharge energy density is independent of the actuator length but increases with the actuation voltage. After actuation, the stall angle of attack of the small flying wing is delayed by 4°, the maximum lift coefficient is increased by 30.9%, and the drag coefficient can be reduced by 17.3%. After the large flying wing is actuated, the stall angle of attack is delayed by 4°, the maximum lift coefficient is increased by 15.1%, but the drag coefficient is increased. The test results of PIV in the flow field of different sections indicate that the stall separation on the surface of the symmetric flying wing starts first from the outer side, and then the separation area begins to appear on the inner side as the angle of attack increases.

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Aerodynamic performance enhancement of a flying wing using nanosecond pulsed DBD plasma actuator

Cited by 29 publications

References 18 publications

Empirical relations for discharge current and momentum injection in dielectric barrier discharge plasma actuators

Empirical relations for discharge current and momentum injection in dielectric barrier discharge plasma actuators

Wind Tunnel Testing of Plasma Actuator with Two Mesh Electrodes to Boundary Layer Control at High Angle of Attack

Experimental Study on Plasma Flow Control of Symmetric Flying Wing Based on Two Kinds of Scaling Models

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