Static and total pressure distributions around a thick delta wing with rounded leading edge

Kawazoe, Hiromitsu; Nakamura, Yu; Ono, Takahiko; Ushimaru, Y.

doi:10.2514/6.1994-2321

Cited by 10 publications

(15 citation statements)

References 1 publication

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“…The results of the axial vorticity contours show that the level of the vorticity decreases 13% in the peak value by increasing the t/C ratio to t/C=0. 19. The velocity vectors also show a decrease in magnitude along with the increase in t/C ratio.…”

Section: Surface Pressure Measurement Resultsmentioning

confidence: 87%

“…As the thickness-to-chord ratio increases to t/C=0. 19, the level of the deterioration significantly increases. There is no clear indication of leading edge vortex and vortex breakdown, which might be due to the localized small-scale separations on the wing surface.…”

Section: Surface and Cross Flow Visualization Resultsmentioning

confidence: 96%

“…Figure 2 At higher angles of attack, CL of thin wing seems to be 0.1 higher and as a main conclusion, it could be stated that the stall condition is observed at a more angle of attack value in the thick wing than the thin one. These values are more than 25 o for the thick wing and a value between 20 o and 25 o for thin wing and Kawazoe et al [19] concluded that angles of attack at stall conditions are different due to the difference in LEV size: for thin delta wing, the vortex size develops wider than thick one. As a result of this fact, vortices coming from both leading edges collide quicker, i.e.…”

Section: Effect Of Thickness-to-chord Ratiomentioning

confidence: 95%

“…The flow over Micro air vehicles (MAV), Unmanned Air Vehicles (UAV) and The effect of thickness-to-chord (t/C) ratio has been studied experimentally and analytically with particular interest in aerodynamic performance of high and moderate swept delta wings [6]- [19]. These studies have mainly reported the thickness effect on aerodynamic forces where global flow field has not been quantified.…”

Section: Motivation Of the Studymentioning

confidence: 99%

“…In these investigations, researchers have mostly studied on basic parameters such as Reynolds number, angle of attack and sweep angle. Although the effect of thickness-to-chord ratio on aerodynamic performance of delta wings have been investigated in some studies in literature [6]- [19], these investigations mainly focus on moderate and high swept delta wings without characterizing the global flow field. As a result, t/C ratio studies have not drawn as much attention as the studies of Reynolds number, angle of attack and sweep angle.…”

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confidence: 99%

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Effect of Thickness-to-Chord Ratio on Flow Structure of a Low Swept Delta Wing

2018

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iv I hereby declare that all information in this document has been obtained and presented in accordance with academic rules and ethical conduct. I also declare that, as required by these rules and conduct, I have fully cited and referenced all material and results that are not original to this work.Low swept delta wings, which are the simplified planforms of Unmanned Air Vehicles (UAVs), Unmanned Combat Air Vehicles (UCAVs) and Micro Air Vehicles (MAVs), have drawn considerable attention in recent years. In order to characterize and improve the operational parameters of these vehicles, the flow physics over low swept delta wings and its control should be well understood.In literature, the effect of thickness-to-chord ratio (t/C) on aerodynamic performance of a delta wing was studied on high and moderate swept delta wings, whereas no attention has been paid on the effect of t/C ratio on global flow structure of low swept delta wings.In the present study, the effect of t/C ratio on flow structure of a delta wing with sweep angle of 35 degree is characterized in a low speed wind tunnel using laser illuminated smoke visualization, near surface and cross-flow particle image velocimetry, and surface pressure measurements. Four delta wing models with t/C vi ratio varying from 4.75 % to 19 % are tested at angles of attack varying from 4 to 10 degrees for Reynolds numbers Re=10,000 and 35,000.The results indicate that the effect of thickness-to-chord ratio on flow structure is quite substantial, such that, as the wing thickness increases, the flow structure transforms from leading edge vortex to three-dimensional separated flow regime.The wing with low t/C ratio of 4.75 % experiences pronounced surface separation at significantly higher angle of attack compared to the wing with high t/C ratio. The results might explain some of the discrepancies reported in previously conducted studies related to delta wings. In addition, it is observed that the thickness of the shear layer separated from windward side of the wing is directly correlated with the thickness of the wing. To conclude, the flow structure on low swept delta wing is highly affected by t/C ratio, which in turn might indicate the potential usage of wing thickness as an effective flow control parameter. Eylül 2017, 89 sayfa İnsansız Hava Araçları (UAV'ler), İnsansız Savaş Hava Araçları (UCAV'ler) ve Mikro Hava Araçlarının (MAV'ler) basitleştirilmiş plan biçimleri olan düşük ok açılı delta kanatlar, son yıllarda büyük ilgi görmektedir. Bu araçların operasyonel parametrelerini karakterize etmek ve geliştirmek için, düşük ok açılı delta kanatlar üzerindeki akış fiziği ve kontrolü iyi anlaşılmalıdır. Literatürde bir delta kanadın aerodinamik performansı üzerindeki kalınlık-veter oranının (t / C) etkisi, yüksek ve orta düzeyde ok açılı delta kanatlar üzerinde incelenirken, t / C oranının düşük ok açılı delta kanatların genel akış yapısı üzerindeki etkisine hiç dikkat edilmemiştir. Bu çalışmada, 35 ° 'lik ok açısına sahip bir delta kanadın akış yapısı üzerindeki t / C ora...

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Section: Surface Pressure Measurement Resultsmentioning

confidence: 87%

Section: Surface and Cross Flow Visualization Resultsmentioning

confidence: 96%

Section: Effect Of Thickness-to-chord Ratiomentioning

confidence: 95%

Section: Motivation Of the Studymentioning

confidence: 99%

mentioning

confidence: 99%

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Effect of Thickness-to-Chord Ratio on Flow Structure of a Low Swept Delta Wing

2018

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Effect of thickness-to-chord ratio on aerodynamics of non-slender delta wing

Ghazijahani

Yavuz

2019

Aerospace Science and Technology

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, 84 pages Flow characterization over delta wings have gained attention in recent decades due to their prevailing usage in designs of unmanned air vehicles (UAVs). In literature, only a few studies have reported wing thickness effect on both the aerodynamic performance and detailed flow structure over delta wings. In the present investigation, the effect of thickness-to-chord (/) ratio on aerodynamics of a non-slender delta wing with 45 degree sweep angle is characterized in a low-speed wind tunnel using laser illuminated smoke visualization, surface pressure measurements, particle image velocimetry, and force measurements. The delta wings with / ratios varying from 2 % to 15 % are tested at broad ranges of angle of attack and Reynolds number. The results indicate that the effect of / ratio on flow structure is quite substantial. Considering the low angles of attack where the wings experience leading edge vortex structure, the strength of the vortex structure increases as the / ratio increases. However, low / ratio wings have pronounced surface separations at higher angle of attack compared to the high / ratio wings. These results are well supported by the force measurements such that high / ratio wings induce higher lift coefficients, CL, at vi low angles of attack, whereas maximum CL values are higher and appear at higher angle of attack for low / ratio wings. This indicates that low / ratio wings are more resistive to the stall condition. Considering the lift-to-drag ratio, CL/CD, increase in / ratio induces remarkable drop in CL/CD values.

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Aerodynamics of non-slender delta and reverse delta wings: Wing thickness, anhedral angle and cropping ratio

Koçak

Yavuz²

2023

Chinese Journal of Aeronautics

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Static and total pressure distributions around a thick delta wing with rounded leading edge

Cited by 10 publications

References 1 publication

Effect of Thickness-to-Chord Ratio on Flow Structure of a Low Swept Delta Wing

Effect of Thickness-to-Chord Ratio on Flow Structure of a Low Swept Delta Wing

Effect of thickness-to-chord ratio on aerodynamics of non-slender delta wing

Aerodynamics of non-slender delta and reverse delta wings: Wing thickness, anhedral angle and cropping ratio

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