Plasma Control of Flow Separation on Swept Wing  at High Angles of Attack

Маслов, А. А.; Sidorenko, A. A.; Zanin, B. Yu.; Postnikov, B. V.; Budovsky, A. D.; Malmuth, N.

doi:10.2514/6.2008-540

Cited by 7 publications

(4 citation statements)

References 4 publications

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“…Most research is devoted to boundary layer separation on a swept wing. In the experiment cited in [12], the control of global separation of the laminar boundary layer that occurs near the leading edge of the swept wing model at high angles of attack was also studied using a single actuator installed in front of the separation region. A significant shift of the separation region downstream was achieved due to boundary layer turbulization.…”

Section: Introductionmentioning

confidence: 99%

3D Turbulent Boundary Layer Separation Control by Multi-Discharge Plasma Actuator

Chernyshev,

Gadzhimagomedov,

Kuryachiy

et al. 2023

Aerospace

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In a subsonic wind tunnel, a three-dimensional separation of a developed turbulent boundary layer was simulated on a swept wing flap model. A multi-discharge plasma actuator operating on the basis of dielectric barrier discharge was used to overcome the positive pressure gradient, leading to a three-dimensional separation, when the ultimate streamline on the aerodynamic surface turns along the flap trailing edge. The actuator created an extended streamwise region of volume force, leading to flow acceleration near a streamlined surface. The influence of the force impact direction relative to the flap trailing edge was studied. The experiments demonstrated that the plasma actuator can significantly influence the flow structure in the separation region, leading to a decrease in both the transverse size of the viscous wake behind the flap and the total pressure losses within it.

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Section: Introductionmentioning

confidence: 99%

3D Turbulent Boundary Layer Separation Control by Multi-Discharge Plasma Actuator

Chernyshev,

Gadzhimagomedov,

Kuryachiy

et al. 2023

Aerospace

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“…The flow field was also investigated by means of flow visualization, and the PIV results indicated that the major contribution to lift enhancement occurred near the wing apex and the vortex above the wing traversed an almost circular path with plasma control. Anatoly Maslov et al [16] investigated the separation control on a model of a swept wing by means of an AC DBD plasma actuator at low speed. Surface pressure measurements and flow visualization indicated that global separation could be mitigated with control.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation on Aerodynamic Control of a Wing with Distributed Plasma Actuators

Han

Liang

et al. 2015

Plasma Sci. Technol.

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Experimental investigation of active flow control on the aerodynamic performance of a flying wing is conducted. Subsonic wind tunnel tests are performed using a model of a 35 o swept flying wing with an nanosecond dielectric barrier discharge (NS-DBD) plasma actuator, which is installed symmetrically on the wing leading edge. The lift and drag coefficient, lift-todrag ratio and pitching moment coefficient are tested by a six-component force balance for a range of angles of attack. The results indicate that a 44.5% increase in the lift coefficient, a 34.2% decrease in the drag coefficient and a 22.4% increase in the maximum lift-to-drag ratio can be achieved as compared with the baseline case. The effects of several actuation parameters are also investigated, and the results show that control efficiency demonstrates a strong dependence on actuation location and frequency. Furthermore, we highlight the use of distributed plasma actuators at the leading edge to enhance the aerodynamic performance, giving insight into the different mechanism of separation control and vortex control, which shows tremendous potential in practical flow control for a broad range of angles of attack.

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“…DBD actuators can be placed in various places on the model surface. DBD power supply (HVG) used in the experiments was the same as used in [7]. HVG is optimized for effective operation (about 5-7% internal loses) in frequency range 500 Hz ÷ 5 kHz but can be operated in range from 20 Hz to 100 kHz with some minor modifications.…”

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confidence: 99%