Plasma Control of Vortex Flow on Delta-Wing at High Angles of Attack

Budovsky, A. D.; Sidorenko, A.A.; Маслов, А. А.; Yu, Boris; Zverkov, I. D.; Postnikov, B. V.; Козлов, В. В.

doi:10.2514/6.2009-888

Cited by 10 publications

(10 citation statements)

References 5 publications

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“…The experiments also showed that the flow continued to be attached in the apex region up to α = 27º. journal.ump.edu.my/ijame ◄ general conclusions are that the characteristics of vortex breakdown depend on wing geometry, Reynolds number and angles of attack [15,16]. Many technical data had been published on blunt leading edge VFE-2 profile in the early 2010s [6,[8][9][10][11].…”

Section: Introductionmentioning

confidence: 90%

Tuft Flow Visualisation on UTM-LST VFE-2 Delta Wing Model Configuration at High Angle of Attacks

Said¹,

Imai²,

Mat³

et al. 2020

IJAME

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This paper reports on flow visualisation and surface pressure measurements over the upper surface of a blunt-edged delta wing model at high angles of attack. The flow structure above the upper surface of the blunt-edged delta wing was found to be different compared to delta wing with sharp leading edge. The flow becomes more complicated especially in the leading edge region of the wing. Currently, there is no data available to verify if the primary vortex could reach the apex of the wing when the angle of attack is further increased. Most prior experiments were performed at the angles of attack, α, below 23° with only a few experiments that had gone to α = 27°. These prior experiments and some CFD works stipulated that the attached flow continue to exist in the apex region of the delta wing even at very high angles of attack above 23°. In order to verify this hypothesis, several experiments at high angles of attack were conducted in Universiti Teknologi Malaysia Low Speed wind Tunnel (UTM–LST), using a specially constructed VFE2 wing model equipped with blunt leading edges. This series of experiments employed two measurement techniques; the first was the long tuft flow visualisation method, followed by surface pressure measurements. The experiments were performed at Reynolds numbers of 1.0×106 and 1.5×106. During these experiments, several interesting flow characteristics were observed at high angles of attack, mainly that the flow became more sensitive to changes in Reynolds number and the angles of attack of the wing. When the Reynolds number increased from 1×106 to 1.5×106, the upstream progression of the initial point of the main vortex was relatively delayed compared to the sharp-edged delta wing. The experiments also showed that the flow continued to be attached in the apex region up to α = 27º.

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Section: Introductionmentioning

confidence: 90%

Tuft Flow Visualisation on UTM-LST VFE-2 Delta Wing Model Configuration at High Angle of Attacks

Said¹,

Imai²,

Mat³

et al. 2020

IJAME

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“…The mechanism of DBD actuators driven by alternating current (AC-DBD) voltage is ion wind, which has been widely used for flow control. [2][3][4][5][6][7] It is widely recognized that the AC-DBD actuators produce an electrohydrodynamic force (EHD). 8 This force results in a near-wall jet with a maximum velocity up to 7 m/s at approximately 0.5 mm above the wall.…”

Section: Introductionmentioning

confidence: 99%

On the effect of operating condition on separated-flow control by nanosecond pulse discharge actuators

Shi

Cheng

et al. 2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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The surface dielectric barrier discharge plasma actuator driven by nanosecond pulses is recognized as an effective fluid actuator for flow separation control. The operation condition of nanosecond dielectric barrier discharge actuators for separated flow control still requires further study, particularly prioritizing the improvement of the effectiveness and reducing energy consumption in flow separation control implementation. In this study, experiments are conducted using a two-dimensional NASA SC(2)-0712 airfoil in a wind tunnel with a Reynolds number of 0.5 Â 10 6 (25 m/s). The pressure measurement experiments show that the location of actuators affects the efficiency of separation control. Particle image velocimetry results indicate that the most efficient location of the actuator is upstream of the separation point and near the original point of the separated shear layer. Meanwhile, the particle image velocimetry results show the vorticity attaches to the airfoil wall after discharge, which suggests that the reattachment is due to the generation of large-scale vortices. These present structures result in the mixing of the shear layer with the main flow thereby delaying separation and reattaching a separated flow. This study shows the most efficient location related to the separation point. Furthermore, it indicates the reattachment of flow is attributed to the motion of vortexes coherent structure.

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“…The first application of DBD plasma for airflow control was published by Roth’s research group. 14 Subsequently, this approach has successfully achieved flow control authority for separation flow for airfoils, 15–18 separation for corners, 19 boundary-layer transition, 20,21 skin-friction reduction 22 and vortical flow on the delta wings, 23,24 even the flight attitudes, 25–27 etc. For the AC-DBD, it is believed that the control mechanism is the tangential wall jet induced by the ionic wind near the typical planar plasma actuator, which adds the momentum into the boundary layer to accelerate the localized flow velocity.…”

Section: Introductionmentioning

confidence: 99%

Flow control for suppression of self-excited rolling oscillation at high angles of attack

Geng

Shi

Cheng

et al. 2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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A cruciform-finned slender body can excite a limit-cycle rolling oscillation at high angles of attack. To suppress the unwanted motions, flow control approaches should be employed if the aerodynamic control surfaces lose control efficiency at high angles of attack. As a promising technology, the ns-dielectric barrier discharge plasma actuator has been successfully used in high-speed and high-Reynolds-number flow control applications. The present work employs a π-type ns-dielectric barrier discharge plasma actuator and vortex generators to suppress self-excited rolling oscillation at α = 50°. The free-to-roll tests show that the plasma actuator ignited at F+ ∼ 1.5 and that the vortex generators can suppress rolling oscillation. The flow patterns from particle image velocimetry measurement at different cross-sections and rolling angles suggest that the vorticity decrease of the leeward vortices may be the control mechanism for the plasma actuator. For the vortex generators, evident modification of the flow field structure can be observed due to the vortices generated from the vortex generators, which decreases the rolling moment induced by the asymmetry vortices to suppress the self-excited rolling oscillation.

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Plasma Control of Vortex Flow on Delta-Wing at High Angles of Attack

Cited by 10 publications

References 5 publications

Tuft Flow Visualisation on UTM-LST VFE-2 Delta Wing Model Configuration at High Angle of Attacks

Tuft Flow Visualisation on UTM-LST VFE-2 Delta Wing Model Configuration at High Angle of Attacks

On the effect of operating condition on separated-flow control by nanosecond pulse discharge actuators

Flow control for suppression of self-excited rolling oscillation at high angles of attack

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