Flow control over swept wings using nanosecond-pulse plasma actuator

Kato, Kentaro; Breitsamter, Christian; Obi, Shinnosuke

doi:10.1016/j.ijheatfluidflow.2016.05.015

Cited by 1 publication

(2 citation statements)

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“…It is emphasized in [13] that the effects of plasma actuators on lift enhancement on a swept wing are quite different as compared to on a straight wing. An experimental study was conducted on the flow control over a NACA 65A005 swept wing model using a single plasma actuator setting near the apex in order to manipulate the leading edge vortices in the post-stall regime.…”

Section: Introductionmentioning

confidence: 99%

“…An experimental study was conducted on the flow control over a NACA 65A005 swept wing model using a single plasma actuator setting near the apex in order to manipulate the leading edge vortices in the post-stall regime. It was shown that the change in the intensity of streamwise vortex due to actuator impact led to the lift enhancement [13]. Because of the weaker manifestation of actuators' impact on three-dimensional flow, the increase in the lift coefficient in the case of a swept wing is one order of magnitude smaller than that in typical two-dimensional flow controls on rectangular wings [14].…”

Section: Introductionmentioning

confidence: 99%

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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%

Section: Introductionmentioning

confidence: 99%