Flow structures in end-view plane of slender delta wing

Şahi̇n, Beşi̇r; Tasci, Mehmet Oguz; Karasu, İlyas; Akıllı, Hüseyin

doi:10.1051/epjconf/201714302099

Cited by 3 publications

(7 citation statements)

References 11 publications

(9 reference statements)

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“…It would be valuable if other flow visualisation techniques can be employed to provide further information on off-surface flow and nature of the vortices at this targeted area. Further discussion on the flow visualisation techniques can be found in [17,21,22]. As for this tuft visualisation method, it is recommended to use more fine strings to obtain better observations.…”

Section: Resultsmentioning

confidence: 99%

“…This causes the delay of primary vortex appearance; in other words, the vortex starts at positions further down the chord, compared to wing with a sharp leading edge. The flow stays attached to the wing surface from the apex to a certain chord-wise position from which the vortex starts, depending on the Reynolds number, angle of attack, Mach number and how blunt the leading-edge profile itself [22][23].…”

Section: Introductionmentioning

confidence: 99%

“…However, the flow visualisation studies on blunt-edged delta wings have discovered many new phenomena which are not fully understood, and thus more experimental explorations are needed. There are only a few studies available [8,22,[26][27] directly related to these efforts. Mat et al [8] performed several series of flow visualisations using the surface oil technique on four different types of leading-edges at certain Reynolds number and angle of attack.…”

Section: Introductionmentioning

confidence: 99%

“…Sahin, et al [22] performed cross-flow studies in end-view planes on delta wing to investigate the consequences of vortex bursting and stall phenomena at the high range of angles of attack but with the influence of yaw angle. Most of the experiments were performed at the angles of attack lower than α =23º.…”

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

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: Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

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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show abstract

“…The conditions under which vortex breakdown occurs are very important to know due to buffeting causing large structural vibrations and severe fatigue damage. There are various parameters affecting the vortex formation on the delta wing, such as angle of attack, yaw angle, sweep back angle, roll angle, the thickness of the wing, leading-edge geometry, Reynolds number, and free-stream conditions (Sahin et al 2017). At the low angle of attack, a double vortex at leading-edge, circulating over the wing apex is formed by the rolling up of the viscous flow sheet [Canpolat et al 2012).…”

Section: Introductionmentioning

confidence: 99%

X-45A Tipi İnsansız Muharebe Hava Aracının Nümerik Olarak İncelenmesi

Soğukpınar

Serkan

2022

UUJFE

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In this paper, the low-speed aerodynamic performance of unmanned combat air vehicle (UCAV) X-45 delta wing was investigated by a numerical method using computational fluid dynamic approaches (CFD). The investigation was conducted with X-45 and the formation of leading-edge vortices (LEV) and vortex breakdown was studied by a varying angle of attack with the range of 5° to 30° at the Reynolds number of 10,000 using the SST turbulence model and are compared with experimental data to validate simulation accuracy of CFD. Stall conditions happened at around 30°, averaged vorticity layer demonstrates a prolonged form that goes along by narrow recirculation zones neighboring to the wing surface. Detail about flow field, including LEV formation, vortex breakdown, interaction, and nonlinear aerodynamic characteristics of X-45 was presented and discussed.

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Numerical Investigation of Flow Characteristics of a Non-Slender Lambda Wing Unmanned Aerial Vehicle

Soğukpınar

Serkan

2022

Adıyaman Üniversitesi Mühendislik Bilimleri Dergisi

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In this paper, the low-speed aerodynamic performance of lambda wing with a chord length of c=210 mm and sweep angle of Λ =51°, thickness 3 mm, and beveled leading edges on the windward side with an angle of 58° is investigated numerically. Reynolds Average Navier Stokes (RANS) theorem equations with Spalart-Allmaras turbulence model were solved up to an angle of attack 45° for incompressible flow around the wing surface and, are compared to experiment to corralete simulation precision of computational fluid dynamic approaches. Detail about the aerodynamic performance of lambda wing including development and formation of the leading-edge vortex (LEV), the interaction of flow with the surface, flow separations, and stall are studied, presented, and discussed. LEV was started at 5°, vortex breakdown was observed at halfway along the leading edge at the angle of 20°, finally, by the time angle is 30°, bursting vortex gives a way to stall stage.

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Flow structures in end-view plane of slender delta wing

Cited by 3 publications

References 11 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

X-45A Tipi İnsansız Muharebe Hava Aracının Nümerik Olarak İncelenmesi

Numerical Investigation of Flow Characteristics of a Non-Slender Lambda Wing Unmanned Aerial Vehicle

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