Opportunities for the integrated use of measurements and computations for the understanding of delta wing aerodynamics

Gursul, Ismet; Allan, Mark; Badcock, K. J.

doi:10.1016/j.ast.2004.08.007

Cited by 27 publications

(11 citation statements)

References 32 publications

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“…The current formulation is similar to the traditional fractional step methods but with two major differences. [15,15] in the streamwise (x) and vertical (y) directions with a grid size of 400 × 200. In both cases, the spatial variables are non-dimensionalized by the mean chordc of the plate.…”

Section: A Numerical Methodsmentioning

confidence: 99%

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Unsteadiness in Flow over a Flat Plate at Angle-of-Attack at Low Reynolds Numbers

Taira

Dickson

Colonius

et al. 2007

45th AIAA Aerospace Sciences Meeting and Exhibit

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Flow over an impulsively started low-aspect-ratio flat plate at angle-of-attack is investigated for a Reynolds number of 300. Numerical simulations, validated by a companion experiment, are performed to study the influence of aspect ratio, angle of attack, and planform geometry on the interaction of the leading-edge and tip vortices and resulting lift and drag coefficients. Aspect ratio is found to significantly influence the wake pattern and the force experienced by the plate. For large aspect ratio plates, leading-edge vortices evolved into hairpin vortices that eventually detached from the plate, interacting with the tip vortices in a complex manner. Separation of the leading-edge vortex is delayed to some extent by having convective transport of the spanwise vorticity as observed in flow over elliptic, semicircular, and delta-shaped planforms. The time at which lift achieves its maximum is observed to be fairly constant over different aspect ratios, angles of attack, and planform geometries during the initial transient. Preliminary results are also presented for flow over plates with steady actuation near the leading edge.

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Section: A Numerical Methodsmentioning

confidence: 99%

“…For this very low Reynolds number of Re = 300, the LEVs are larger compared to ones from higher Reynolds number flow. 15 One can observe transient behavior of the wake until t ≈ 15 in Figure 11. Beyond this point in time, there are some unsteady shedding of small vortical structures behind the rolled up vortices.…”

Section: B Effect Of Planform Geometrymentioning

confidence: 96%

Unsteadiness in Flow over a Flat Plate at Angle-of-Attack at Low Reynolds Numbers

Taira

Dickson

Colonius

et al. 2007

45th AIAA Aerospace Sciences Meeting and Exhibit

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“…Increasing the angle of attack [7] is one of the dominant sources that cause to formation of vortex breakdown and affects [3,8] the whole flow regime around the wing. Vortex breakdown structure includes strong reversed flow [9][10] that occurs on sudden expansion of leading-edge vortices at a critical angle of attack [11][12] in unsteady flows. In that case, turbulent intensity [13] increases rapidly and leading-edge vortex kinetic energy is [10] transferred into kinetic energy of small vortices and turbulent kinetic energy.…”

Section: Introductionmentioning

confidence: 99%

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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“…For further information about vortex meandering, refer to [8][9][10]. The vortex breakdown and its effect on the performance of aerodynamic systems and flow characteristics on the wing were studied by several authors [11][12][13][14][15][16][17]. The flow over a slender delta wing demonstrates a profound viscous effect at low Reynolds numbers, Re=10 3 -10 4 .…”

Section: Introductionmentioning

confidence: 99%

Salınım hareketinin sapma açısı altındaki bir delta kanada etkileri

Tasci¹,

Tümse²,

Şahi̇n³

et al. 2020

Ömer Halisdemir Üniversitesi Mühendislik Bilimleri Dergisi

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In this study, the main objective is to reveal the change of the vortical flow characteristics on a slender delta wing with a sweep angle of Λ=70º under the alteration of three different sideslip angles of β=0º, 4º, and 8º at three different main angles of attack of αm=25º, 30º and 35º experimentally. Dye visualization experiments were conducted at a Reynolds number of Re=2x10 4 to analyze qualitatively. The perturbation motion which has amplitudes of α0=±0.5º and ±1º was applied continuously under the periods of time of Te=0.5s, 1s, and 2s. However, the effects of the lowfrequency perturbations to which the aircraft is exposed during the maneuver were examined. It is observed that Kelvin-Helmholtz in the case of the perturbed motion vortices is more prominent than static case results of the slender delta wing. The vortex breakdown location on the perturbed delta wing has been changed in a wider range than the static case of the delta wing at zero sideslip angle, β.Bu çalışmada, süpürme açısı Λ=70º olan narin (slender) delta kanadın girdaplı akış yapısındaki değişimi, sapma açısı β=0º, 4º ve 8º karşısındaki değişimi, üç farklı ortalama hücum açısında αm =25º, 30º ve 35º boya deneyi incelemesi amaçlanmıştır. Boya ile nitel görselleştirme deneyleri, Re=2x10 4 gerçekleştirilmiştir. Kanat modeli istenilen açıda sabitlenerek ve elde edilen deney sonuçlar dikkate alınarak, α0=±0.5º ve ±1º genliğinde ve Te =0.5s, 1s ve 2s periyotlarında kanata sürekli salınım hareketi verilerek girdap çökmesinin belirli ölçüde kontrolü sağlanmaya çalışılmıştır. Ancak, uçağın manevra sırasında maruz kaldığı düşük frekanslı bozulmaların etkileri incelenmiştir. Kelvin-Helmholtz girdaplarının narin delta kanadın daimî salınım hareketi verilen durumunda statik vaka sonuçlarından daha belirgin olduğu gözlenmektedir. Narin delta kanatlarının sıfır sapma açısı, β salınımı hareketi anında; girdap çökme konumu statik durumdan daha geniş bir aralıkta ileri ve geri hareket etmektedir.

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Opportunities for the integrated use of measurements and computations for the understanding of delta wing aerodynamics

Cited by 27 publications

References 32 publications

Unsteadiness in Flow over a Flat Plate at Angle-of-Attack at Low Reynolds Numbers

Unsteadiness in Flow over a Flat Plate at Angle-of-Attack at Low Reynolds Numbers

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

Salınım hareketinin sapma açısı altındaki bir delta kanada etkileri

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