Effect of a centerbody on the vortex flow of a double-delta wing with leading edge extension

Sohn, Myung-Hwan; Chang, Jo Won

doi:10.1016/j.ast.2009.11.004

Cited by 11 publications

(5 citation statements)

References 15 publications

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“…But they can cause fatigue failures and disturb overall flow regime around the wing. A relation is detected between LEX vortices and wing vortices in a study about delta wing [29]. Each of vortices can influence the other in the same manner, but also, they behave separately.…”

Section: Introductionmentioning

confidence: 90%

Investigation of Flow Characteristics and Vortex Formations of Lambda Wing at High Angles of Attack

Yavuz¹

2020

Journal of Thermal Engineering

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It is well known in literature that further stages of flow separation and vortex breakdown around wings can be able to cause stall of wings. These formations must be investigated carefully for new plane types. However, some limited studies are available, especially on lambda wing for high angles of attack. In this study, effect of angle of attack on flow characteristics and vortex breakdown around a lambda wing is investigated with a constant Reynolds number of 10000. Computational fluid dynamic analysis is used and results of high angles of attack of the wing are given up to 45 0 which are not available in literature. Open water channel simulation is used. Vortex breakdown initially begins at an angle of 17 0 and it almost reaches to tip of wing when angle of attack is equal to 25 0. Vortices get stronger at further increments of angle of attack and they become to nearly equal length of wing at 45 0. Rounding effect of leading edges is investigated for decreasing vortex magnitudes. Streamline, particle injection, iso-value of vortices and location of stagnation points are given, and they are discussed in detail.

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Section: Introductionmentioning

confidence: 90%

Investigation of Flow Characteristics and Vortex Formations of Lambda Wing at High Angles of Attack

Yavuz¹

2020

Journal of Thermal Engineering

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“…Several scientists have explored the rolled-up vortex effect on different wings. Sohn et al [7] have investigated the effect of a center body on the vortex flow of a double-delta wing with leading edge extension. Heyes and Smith have studied, in depth, the modification of a wing tip vortex by vortex generators [8].…”

Section: Introductionmentioning

confidence: 99%

Vortex Dynamics Study of the Canard Deflection Angles’ Influence on the Sukhoi Su-30-Like Model to Improve Stall Delays at High AoA

et al. 2019

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The maneuverability of the Sukhoi Su-30 at very high angles of attack (AoA) was remarkably appealing. Canard angle, in cooperation with aircraft wing, created a flow pattern whereby, in that position, the fighter still had as much lifting force as possible in order not to stall. The behavior of changing canard angle configuration played an essential role in creating the strong vortex core so that it could delay the stall. The study of vortex dynamics at canard deflection angle gave an essential function in revealing the stall delay phenomenon. In this study, one could analyze the flow patterns and vortex dynamics ability of the Sukhoi Su-30-like model to delay stall due to the influence of canard deflection. The used of water tunnel facilities and computational fluid dynamics (CFD) based on Q-criterion has obtained clear and detailed visualization and aerodynamics data in revealing the phenomenon of vortex dynamics. It was found that between 30° and 40° canard deflection configurations, Sukhoi Su-30-like was able to produce the most robust flow interaction from the canard to the main wing. It was clearly seen that the vortex merging formation above the fighter heads was clearly visible capable of delaying stall until AoA 80°.

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“…The main vortices in cross flow planes take place in the inner side close to the central axis of the delta wing. Sohn and Chang [10] investigated the effect of centerbody on a yawed double delta wing by using off-surface flow visualization and wing-surface pressure measurements. It is concluded that up to 24° angle of attack, α the presence of the centerbody have a small influence on the suction pressure distribution over the upper wing surface, even at the large yaw angle of β=20°.…”

Section: Introductionmentioning

confidence: 99%

Dye Visualization of a Yawed Slender Delta Wing

Karasu¹

2015

Journal of Thermal Engineering

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In the present experimental study, effects of yaw angle, β on the flow structure at high angles of attack, α with 70° sweep angle, Λ were investigated using the dye visualization technique. In the case of zero yaw angle, β a pair of leading edge vortices take place on both sides of cords axis are more or less symmetrical over the delta wing. These symmetrical vortical flow structures start deteriorating when angle yaw, β is introduced. Onset of vortex breakdown location on the windward side occurs further upstream, on the other hand, the leading edge vortex on the leeward side breaks down further downstream. A perceivable interactions are consisted between structures of vortical flows developed from pair of leading edge vortices after onset of vortex breakdowns. It can be concluded that the magnitude of the leading-edge vortices, onset of vortex breakdowns, and formation of unsteady flow structures generated after vortex breakdowns are substantially affected by yaw angle, β. Angles, θ1 and θ2 between centerline of the delta wing and both central axes of spiral vortices vary as a function of yaw angle, β.

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Effect of a centerbody on the vortex flow of a double-delta wing with leading edge extension

Cited by 11 publications

References 15 publications

Investigation of Flow Characteristics and Vortex Formations of Lambda Wing at High Angles of Attack

Investigation of Flow Characteristics and Vortex Formations of Lambda Wing at High Angles of Attack

Vortex Dynamics Study of the Canard Deflection Angles’ Influence on the Sukhoi Su-30-Like Model to Improve Stall Delays at High AoA

Dye Visualization of a Yawed Slender Delta Wing

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