Flow structure over the yawed nonslender diamond wing

Şahi̇n, Beşi̇r; Yayla, Sedat; Canpolat, Çetin; Akıllı, Hüseyin

doi:10.1016/j.ast.2011.06.008

Cited by 28 publications

(13 citation statements)

References 27 publications

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“…A detailed analysis of the flow above the delta wing was made, including velocity and Reynolds stresses distribution. Yayla et al [12] and Sahin et al [13] studied the vortical structure over lambda and diamond wings respectively, providing detailed information about Reynolds stresses and turbulence kinetic energy. Conpolat et al [14] conducted an experimental study, investigating the vortical flow structure over a delta wing at various angles of attack and yaw angles, also including Reynolds stresses distributions and turbulence kinetic energy.…”

Section: Introductionmentioning

confidence: 99%

Turbulence Kinetic Energy Balance in the Wake of a Sharp-edged Highly Swept Delta Wing

Panagiotou

Sideridis

Yakinthos

et al. 2015

Flow Turbulence Combust

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Hot-wire measurements in the wake of a flat plate delta wing, at a fixed angle of attack, were carried-out in order to investigate its turbulence kinetic energy budget. The purpose of this study is to help acquire more information about the vortex structure formed in the wake region of the delta wing and to provide data for turbulence models' validation. Point measurements were conducted in five planes perpendicular to the flow, on a high spatial resolution two-dimensional measurement grid that allowed precise derivative calculations of the flow quantities needed for the derivation of the kinetic energy budget. The turbulence kinetic energy convection, production, viscous diffusion and turbulence diffusion terms were directly obtained from the experimental data, whereas dissipation and pressure diffusion terms were calculated indirectly using techniques presented and validated in previous studies. All of the terms of the turbulence kinetic energy budget, along with the velocity components and the Reynolds stresses, are presented and discussed.Keywords Delta wing · Hot-wire anemometry · Measurement · Turbulence kinetic energy balance · Vortex breakdown · Wake NomenclatureEnglish symbols C k convection term of the TKE budget D p pressure diffusion term of the TKE budget D t turbulence diffusion term of the TKE budget D v viscous diffusion term of the TKE budget e iso isotropic expression for the dissipation term of the TKE budget k turbulence kinetic energy per unit mass

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Section: Introductionmentioning

confidence: 99%

Turbulence Kinetic Energy Balance in the Wake of a Sharp-edged Highly Swept Delta Wing

Panagiotou

Sideridis

Yakinthos

et al. 2015

Flow Turbulence Combust

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“…In order to determine results of this interaction, the near surface topology of a generic delta wing is investigated by Yavuz et al 8 by utilizing two dimensional particle image velocimetry. Moreover, Sahin et al 5 and Yayla et al 9 also performed measurements close to the surface of lambda and diamond wings using stereoscopic particle image velocimetry (stereo-PIV). They concluded that flow topology and corresponding unsteady flow features are directly influenced with angle of attack,  which defines the location of vortex breakdown.…”

Section: Introductionmentioning

confidence: 98%

Effects of Perturbation on the Flow over Nonslender Delta Wings

Canpolat

Şahi̇n

Yayla

et al. 2015

45th AIAA Fluid Dynamics Conference

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An experimental investigation is presented to reveal the flow physics and turbulence statistics of nonslender delta and diamond wings with a sweep angle of  = 40 under perturbation condition with the amplitude of α =  +αsinet = ±0.5 during Te=2/e= 0.5s. The experiments are carried out using the techniques of dye visualization and Stereoscopic Particle Image Velocimetry (stereo-PIV) on the plan view and cross flow plane for the cases of stationary and perturbed wing as the angle of attack is varied within 7 o ≤≤17 o . In order to perform a comparison based on the wing planform, diamond wing is designed from the composition of same shape of the delta wing and an attachment part mounted on its trailing edge. This study also provides information about effects of trailing edge attachment mounted on a generic nonslender delta wing under current test conditions. It can be concluded that perturbation is beneficial in the control of flow over both wings at relatively high angles of attack, .The duration required for occurrence of flow control increases for the current period and time of perturbation, when the trailing edge attachment (diamond wing case) is employed. Beyond this, trailing edge attachment takes role in attenuation of turbulence statistics, where leading edge vortex breaks down. Nomenclature  = angle of attack, deg  = mean angle of attack, deg e = angular velocity of wing perturbation, rad/s Te = period of wing perturbation, s fe = perturbation frequency of the wing, s a(t) = dynamic angle of attack of the wings, deg U = free stream flow velocity, mm/s C' = chord of delta wing, mm C = chord of diamond wing, mm Λ = sweep angle, deg Ψ = stream function ω = vorticity 1 *Assist. Professor, 2 t = time (s) TKE = turbulence kinetic energy wRMS = RMS of vertical velocity fluctuation Re = Reynolds number based on chords of the wings <> = time-averaged quantitiy x= distance from the wing apex measured in the free-stream flow direction y = distance from the chord axis in transverse direction

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“…They proved that flow structure and development of vortex breakdown profoundly are affected by angle of attack, α. [6] demonstrated that structures of vortex bursting and vortical flow over a non-slender diamond wing are sensitively effected by yaw angle, β using dye visualization and the PIV technique and time averaged flow data over the wing surface changes profoundly increasing over the yaw angle, β=6°.…”

Section: Introductionmentioning

confidence: 99%

Flow Behavior in Side-View Plane of Pitching Delta Wing

et al. 2018

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In the present investigation, a delta wing which has 70° sweep angle, Λ was oscillated on its midcord according to the equation of α(t)=α m +α o sin(ω e t). This study focused on understanding the effect of pitching and characterizing the interaction of vortex breakdown with oscillating leading edges under different yaw angles, β over a slender delta wing. The value of mean angle of attack, α m was taken as 25°. The yaw angle, β was varied with an interval of 4° over the range of 0°≤β≤ 16°. The delta wing was sinusoidally pitched within the range of period of time 5s≤T e ≤60s and reduced frequency was set as K=0. 16, 0.25, 0.49, 1.96 and lastly amplitude of pitching motion was arranged as α o =±5°.Formations and locations of vortex breakdown were investigated by using the dye visualization technique in side view plane.

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Flow structure over the yawed nonslender diamond wing

Cited by 28 publications

References 27 publications

Turbulence Kinetic Energy Balance in the Wake of a Sharp-edged Highly Swept Delta Wing

Turbulence Kinetic Energy Balance in the Wake of a Sharp-edged Highly Swept Delta Wing

Effects of Perturbation on the Flow over Nonslender Delta Wings

Flow Behavior in Side-View Plane of Pitching Delta Wing

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