Experimental investigation of lift enhancement for flying wing aircraft using nanosecond DBD plasma actuators

Yao, Junkai; Zhou, Danjie; He, Haibo; He, Chengjun; Shi, Zhiwei; Du, Hai

doi:10.1088/2058-6272/aa57f1

Cited by 4 publications

(4 citation statements)

References 21 publications

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“…1 , which is of the same order as the vortex shedding frequency. This particular frequency can cause a strong coupling between the flow induced by plasma actuation and the free-stream, which strengthens the energy injected into the downstream and stabilizes the shedding vortex, resulting in the reattachment of the flow [26].…”

Section: Flying Wing Model Aerodynamic Datummentioning

confidence: 99%

Analysis of flow separation control using nanosecond-pulse discharge plasma actuators on a flying wing

Shi

et al. 2018

Plasma Sci. Technol.

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Dielectric barrier discharge (DBD) plasma is one of most promising flow control method for its several advantages. The present work investigates the control authority of nanosecond pulse DBD plasma actuators on a flying wing model's aerodynamic characteristics. The aerodynamic forces and moments are studied by means of experiment and numerical simulation. The numerical simulation results are in good agreement with experiment results. Both results indicate that the NS-DBD plasma actuators have negligible effect on aerodynamic forces and moment at the angles of attack smaller than 16°. However, significant changes can be achieved with actuation when the model's angle of attack is larger than 16°where the flow separation occurs. The spatial flow field structure results from numerical simulation suggest that the volumetric heat produced by NS-DBD plasma actuator changes the local temperature and density and induces several vortex structures, which strengthen the mixing of the shear layer with the main flow and delay separation or even reattach the separated flow.

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Section: Flying Wing Model Aerodynamic Datummentioning

confidence: 99%

Analysis of flow separation control using nanosecond-pulse discharge plasma actuators on a flying wing

Shi

et al. 2018

Plasma Sci. Technol.

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“…When plasma actuation is applied to the leading edge of the inner and middle wing, the control effect is obvious. The actuation effect is best when the corresponding dimensionless frequency is 1 under low frequency conditions, and the variation of actuation voltage has little effect on the effect of the lift increasing [30].…”

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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“…It has attracted wide attention in recent years and is widely used in biomedicine [12][13][14][15][16], environmental purification [17][18][19][20], catalytic technology [21][22][23][24], material handling [25][26][27], flow control, and other fields. Surface Dielectric Barrier Discharge (SDBD) [28] which has the advantages of easy adhesion, rapid response, and adjustable parameters, has been widely used in the fields of stall control [29][30][31][32][33][34], boundary layer rotation [35][36][37][38][39][40], lift enhancement [41][42][43], anti-icing [44][45][46][47][48] and other flow separation control applications. Surface dielectric barrier discharge is classified as Alternating Current Dielectric Barrier Discharge (AC-DBD), Microsecond Dielectric Barrier Discharge (µS-DBD), and Nanosecond Dielectric Barrier Discharge (NS-DBD), of which AC-DBD and NS-DBD are more widely used than µS-DBD.…”

Section: Introductionmentioning

confidence: 99%

Flow Separation Control of Nacelle Inlets in Crosswinds by Dielectric Barrier Discharge Plasma Actuation

et al. 2023

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Crosswinds will lead to large-scale flow separation in the nacelle inlets, which seriously affects the flight safety of the aircraft; there is an urgent need to develop flow control measures. As a plasma flow control method, the application of surface dielectric barrier discharge in the field of nacelle inlet separation control is of great significance for improving the intake quality. Based on the characteristic law of the baseline flow field, the flow control effect of the nacelle inlet separation flow field experiments with NS-DBD, and the influence of the actuation frequency on the flow control is discussed. A comparative experimental study of NS-DBD and AC-DBD is carried out. Finally, the flow control mechanisms for both are discussed. The results show that under the condition that the flow velocity of the wind tunnel is 35 m/s and the crosswind angle is 10°, the average total pressure loss coefficient and distortion index decrease by 29.62% and 44.14% by NS-DBD actuation. At the same time, exists an inherent optimal coupling frequency in NS-DBD, and the control effect of NS-DBD is better than that of AC-DBD. NS-DBD mainly through shock waves and induced vortices, while AC-DBD mainly through the induced generation of near-wall jets to reduce the inverse pressure gradient and improve nacelle flow separation.

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Experimental investigation of lift enhancement for flying wing aircraft using nanosecond DBD plasma actuators

Cited by 4 publications

References 21 publications

Analysis of flow separation control using nanosecond-pulse discharge plasma actuators on a flying wing

Analysis of flow separation control using nanosecond-pulse discharge plasma actuators on a flying wing

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

Flow Separation Control of Nacelle Inlets in Crosswinds by Dielectric Barrier Discharge Plasma Actuation

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