Unsteady aerodynamics of nonslender delta wings

Gursul, Ismet; Gordnier, Raymond E.; Visbal, Miguel R.

doi:10.1016/j.paerosci.2005.09.002

Cited by 276 publications

(163 citation statements)

References 90 publications

(158 reference statements)

Supporting

Mentioning

150

Contrasting

Order By: Relevance

“…The stalling angle for X-45 wing is α=32 o , where the lift coefficient starts to decrease dramatically. Moreover, the lift coefficient increases with increasing sweep angle as reported by [1]. The stall occurs around α=25 o for generic delta wing with sweep angle of Λ=45 o .…”

Section: Resultssupporting

confidence: 64%

“…Vortical flow over the wings develop at very low angles of attack, and form close to the wing surface as also indicated by [1]. However, the leading edge vortices (LEVs) take place further away from the surface of the slender delta wing compared to the present wings [23][24].…”

Section: Resultsmentioning

confidence: 70%

“…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].…”

Section: Introductionmentioning

confidence: 99%

“…However, aerodynamic characteristics of non-slender wings are rarely found in the literature. They have lower maximum lift coefficient with lower stall angle than slender wings [1]. [13] determined lift and drag coefficients of UCAV 1303 model, which is built on a lambda planform under various magnitudes of angle of attack and yaw angle.…”

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

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: 64%

Section: Resultsmentioning

confidence: 70%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

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

“…The structure of the flow over a non-slender delta wing differs substantially from that over a slender delta wing. 1 A reduction of Λ from, e.g., 65…”

Section: Introductionmentioning

confidence: 99%

Effects of Leading-Edge Radius on Aerodynamic Characteristics of 50º Delta Wings

Verhaagen

2010

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

View full text Add to dashboard Cite

The study focuses on the effects of the leading-edge radius on the flow over 50 o swept delta wing models. Three models were tested, one model having a sharp leading edge and the other two having a semi-circular leading edge of different radius. The vortical flow on and off the surface of the models was investigated using an oil-flow visualization and a Stereo Particle Image Velocimetry (SPIV) technique. The leading-edge radius is shown to affect the size and location of the vortices and also the vortex bursting location over the models. As a result of this, the leadingedge radius also affects the forces and moment acting on a 50 o delta wing.

show abstract

High Angle of Attack Aerodynamics

Gursul

Wang

2010

Encyclopedia of Aerospace Engineering

View full text Add to dashboard Cite

In this chapter, low‐speed aerodynamics of highly swept wings is discussed. Highly swept wings, known as delta wings, can fly at high angle of attack without stall. This quality is invaluable for military aircraft during a high angle of attack maneuver. Leading‐edge vortices develop on highly swept wings as a result of flow separation and contribute to the lift force. Highly energetic vortices break down or burst at high angles of attack, resulting in highly unsteady flows. Vortex breakdown may cause wing or fin vibrations, called buffeting, which is the structural response due to the unsteady flow. Aircraft configurations may have forebody vortices, leading‐edge vortices that originate from strakes, and the main wing vortices, which may interact with each other during a maneuver. Leading‐edge vortices in unsteady flows exhibit substantial time lag and hysteresis effects. They may also cause self‐induced roll oscillations of aircraft, known as wing rock. Finally, vortex control techniques are briefly discussed.

show abstract

Unsteady aerodynamics of nonslender delta wings

Cited by 276 publications

References 90 publications

Aerodynamics and Flow Characteristics of X-45 Delta Wing Planform

Aerodynamics and Flow Characteristics of X-45 Delta Wing Planform

Effects of Leading-Edge Radius on Aerodynamic Characteristics of 50º Delta Wings

High Angle of Attack Aerodynamics

Contact Info

Product

Resources

About