Observation of the Vortical Flow over a Yawed Delta Wing

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

doi:10.1061/(asce)as.1943-5525.0000163

Cited by 24 publications

(8 citation statements)

References 30 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…3a, a low velocity region occupies the whole surface of the wing in the cases of high angle of attack. They occur due to the three dimensional instability of the shear layer separating from the surface of wings [2]. These vortices have an elongated form, which can be also understood from corresponding dye visualization experiments presented in Figure 3a.…”

Section: Resultssupporting

confidence: 54%

“…High structural strength and lift are the other features of the delta wings, which have been employed for various missions, especially in combat aerial vehicles [1]. The flow over delta wings can be characterized by a pair of leading edge vortices emanating from wing apex [2]. Boundary layer separation causes these vortical structures formed by rolling up of viscous flow sheet.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Aerodynamics and Flow Characteristics of X-45 Delta Wing Planform

Yanıktepe¹,

Özalp²,

Canpolat³

2016

KSU J. Eng. Sci.

View full text Add to dashboard Cite

ABSTRACT:The present experimental work investigates the near surface flow structure and aerodynamic characteristics of X-45 type non-slender delta wing planform using dye visualization, Stereoscopic Particle Image Velocimetry (stereo-PIV) and aerodynamic load measurements. The instantaneous images are acquired on the planview plane within 5 o ≤ α ≤ 20 o to calculate the time-averaged flow data. In order to compare flow structures with other non-slender wing planforms such as delta and lambda, previously presented dye visualization and stereo-PIV results are also provided. It can be concluded that vortical flow with a pair of well-defined LEVs over X-45 develop at very low angles of attack, and form close to the wing surface similar to delta and lambda planforms. The stall occurs at an angle of attack α = 32 o , whereas stalling is evident at relatively lower angles of attack for simple delta wing. Keywords: Aerodynamics, delta wing, stereo-PIV, X-45 X-45 Tipi Delta Kanat Modeli Üzerinde Oluşan Akış Karakteristikleri ve AerodinamiğiÖZET: Mevcut deneysel çalışma ile X-45 tipi delta kanat modeli üzerinde oluşan yakın yüzey akış yapısı ve aerodinamik karakteristikleri, boya görüntüleme, üç boyutlu Stereoskopik Parçacık Görüntüleme Tekniği (stereo PIV) ve aerodinamik kuvvet ölçümleri kullanılarak araştırılmıştır. Anlık görüntüler ile üst görünüş düzleminde zaman ortalama akış verileri 5 o ≤ α ≤ 20 o hücum açılarında elde edilmiştir. Delta ve Lamda tipi diğer düşük süpürme açılarına sahip delta kanat modelleri ile akış yapılarını karşılaştırmak için önceki sunulan boya görüntüleri ve stero-PIV sonuçları kullanılmıştır. Düşük hücum açılarında X-45 tipi delta kanat modeli üzerinde iyi tanımlanmış ön uç yanal girdaplar delta ve lamda modellerine benzer kanat yüzeyinde oluşmaktadır. X-45 tipi delta kanat modelinde ölü akış yapısı α = 32 o de oluşmaktayken basit delta kanat ve lamda modellerinde daha düşük hücum açılarında meydana gelmektedir.

show abstract

Section: Resultssupporting

confidence: 54%

Section: Introductionmentioning

confidence: 99%

Aerodynamics and Flow Characteristics of X-45 Delta Wing Planform

Yanıktepe¹,

Özalp²,

Canpolat³

2016

KSU J. Eng. Sci.

View full text Add to dashboard Cite

show abstract

“…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. Studies considering the turbulence field of a delta wing, such as the latter ones mentioned above, are useful not only in acquiring information about the delta wing vortex structure, but also for procedures aimed at turbulence models validation.…”

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

View full text Add to dashboard Cite

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

show abstract

“…17 There is no sideslip (yaw) angle, thus the flow field must be considered to be symmetric on center line of the wing as indicated by Canpolat et al. 28 Therefore, only half of the wing is covered by the computational domain. The simulations were performed on an unstructured grid (Figure 3) which had approximately 7.0 × 10 6 cells and was obtained after excessive simulation for grid independence study.…”

Section: Methodologiesmentioning

confidence: 99%

Computational investigation of the flow structure over a pitching delta wing at supersonic speeds

Hadidoolabi

Ansarian

2015

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

Compressible flows over a 60° sweep delta wing with a sharp leading edge undergoing pitching oscillations are computationally studied. Emphasis in this study is on possible supersonic flow structures and their variations during the pitching motion of a delta wing. Unstructured grid, k-ωSST turbulence model and a dual-time implicit time integration are used. Accurate simulations are performed for various Mach number and angles of attack to cover different flow structures and phenomena associated with them. Variations of flow patterns in a crossflow plane, pressure coefficient on the wing surface, and hysteresis loops associated with vortex core location during a pitching cycle are investigated. The trends with Mach number, mean angle of attack, amplitude of pitching and pitching frequency are illustrated.

show abstract

Observation of the Vortical Flow over a Yawed Delta Wing

Cited by 24 publications

References 30 publications

Aerodynamics and Flow Characteristics of X-45 Delta Wing Planform

Aerodynamics and Flow Characteristics of X-45 Delta Wing Planform

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

Computational investigation of the flow structure over a pitching delta wing at supersonic speeds

Contact Info

Product

Resources

About