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

Ghazijahani, Mohammad Sharifi; Yavuz, Mehmet Metin

doi:10.1016/j.ast.2019.03.033

Cited by 13 publications

(3 citation statements)

References 57 publications

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“…In another numerical calculation, Synthetic jet control of the asymmetrical flow field of the flying wing for an UAV was investigated and the study showed that synthetic jet control cannot effectively improve the effect of asymmetrical vortex on the lateral aerodynamic characteristic of the model in zero sideshift [14] on the other hand, in a PIV experiment system, The flow structures and aerodynamic performance of a thin delta wing with a sweep angle of 65 degrees are equipped with needle vortex generators was studied and findings were compared with smooth wing [15] study showed that the acicular wing delays eddy distortion compared to a straight wing. In a wind tunnel experiment, the effect of the thickness-chorus (t/C) ratio on the aerodynamics of a non-thin delta wing with a sweep angle of 45 degrees was characterized and results indicated that the effect of ratio on flow structure was quite substantial [16].…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation of Flow Characteristics of a Non-Slender Lambda Wing Unmanned Aerial Vehicle

Soğukpınar

Serkan

2022

Adıyaman Üniversitesi Mühendislik Bilimleri Dergisi

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In this paper, the low-speed aerodynamic performance of lambda wing with a chord length of c=210 mm and sweep angle of Λ =51°, thickness 3 mm, and beveled leading edges on the windward side with an angle of 58° is investigated numerically. Reynolds Average Navier Stokes (RANS) theorem equations with Spalart-Allmaras turbulence model were solved up to an angle of attack 45° for incompressible flow around the wing surface and, are compared to experiment to corralete simulation precision of computational fluid dynamic approaches. Detail about the aerodynamic performance of lambda wing including development and formation of the leading-edge vortex (LEV), the interaction of flow with the surface, flow separations, and stall are studied, presented, and discussed. LEV was started at 5°, vortex breakdown was observed at halfway along the leading edge at the angle of 20°, finally, by the time angle is 30°, bursting vortex gives a way to stall stage.

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Section: Introductionmentioning

confidence: 99%

Numerical Investigation of Flow Characteristics of a Non-Slender Lambda Wing Unmanned Aerial Vehicle

Soğukpınar

Serkan

2022

Adıyaman Üniversitesi Mühendislik Bilimleri Dergisi

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“…Meanwhile, non-slender wing having low to moderate sweep angle (Λ ≤ 55°). Most of the delta wing UAV has been designed in the non-slender configuration (Gursul et al , 2005; Brett and Ooi, 2014; Ghazijahani and Yavuz, 2019). Therefore, the study of non-slender delta wing is important for future UAV development.…”

Section: Introductionmentioning

confidence: 99%

Propeller locations study of a generic delta wing UAV model

Kasim¹,

Mat²,

Ishak³

et al. 2020

AEAT

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Purpose This study aims to investigate the effects of propeller locations on the aerodynamic characteristics of a generic 55° swept angle sharp-edged delta wing unmanned aerial vehicle (UAV) model. Design/methodology/approach A generic delta-winged UAV model has been designed and fabricated to investigate the aerodynamic properties of the model when the propeller is placed at three different locations. In this research, the propeller has been placed at three different positions on the wing, namely, front, middle and rear. The experiments were conducted in a closed-circuit low-speed wind tunnel at speeds of 20 and 25 m/s corresponding to 0.6 × 106 and 0.8 × 106 Reynolds numbers, respectively. The propeller speed was set at constant 6,000 RPM and the angles of attack were varied from 0° to 20° for all cases. During the experiment, two measurement techniques were used on the wing, which were the steady balance measurement and surface pressure measurement. Findings The results show that the locations of the propeller have significant influence on the lift, drag and pitching moment of the UAV. Another important observation obtained from this study is that the location of the propeller can affect the development of the vortex and vortex breakdown. The results also show that the propeller advance ratio can also influence the characteristics of the primary vortex developed on the wing. Another main observation was that the size of the primary vortex decreases if the propeller advance ratio is increased. Practical implications There are various forms of UAVs, one of them is in the delta-shaped planform. The data obtained from this experiment can be used to understand the aerodynamic properties and best propeller locations for the similar UAV aircrafts. Originality/value To the best of the author’s knowledge, the surface pressure data available for a non-slender delta-shaped UAV model is limited. The data presented in this paper would provide a better insight into the flow characteristics of generic delta winged UAV at three different propeller locations.

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“…The UAV industry is growing rapidly, including the delta-planform UAVs. Therefore, many studies have been conducted to study the effects of flow control on the delta wing [11]. Flow control techniques (active and passive) had been implemented on the delta wing to improve the vortex properties and delay the vortex breakdown [12].…”

Section: Introductionmentioning

confidence: 99%

Effects of the Propeller Advance Ratio on Delta Wing UAV Leading Edge Vortex

Kasim

Segard

Mat

et al. 2019

IJAME

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Delta wing is a triangular-shaped platform that can be applied into the unmanned aerial vehicle (UAV) or drone applications. However, the flow above the delta wing is governed by complex leading-edge vortex structures which result in complicated aerodynamics behaviour. At higher angles of attack, the vortex burst can take place when the swirling flow is unable to sustain the adverse pressure gradient. More studies are needed to understand these vortex phenomena. This paper addresses an experimental study of active flow control called propeller on a generic 55° swept angle sharp-edged delta wing model. In this experiment, a propeller was placed at two different locations. The first location was at the apex of the wing while the second position was at the rear of the wing. The experiments were conducted in a 1.5 × 2.0 m2 closed-loop wind tunnel facility at Universiti Teknologi Malaysia. The freestream velocities were set at 20 m/s and 25 m/s. The research consisted of an intensive surface pressure measurement above the wing surface to investigate the effects of rotating propeller towards the leading-edge vortex. The experiments were divided into four configurations. The clean wing configuration was performed without the propeller and followed by pusher-propeller configuration using 10-inch 9-inch propellers. The final configuration was the tractor-propeller with a 10-inch propeller. The results emphasise the influences of the propeller size and its location corresponding to vortex properties above the delta-winged UAV model. The findings had indicated that the vortex peak is increased when the propeller is installed for both pusher and tractor configurations. The results also indicate that the pressure coefficient is increased when the propeller advance ratio increases.

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

Cited by 13 publications

References 57 publications

Numerical Investigation of Flow Characteristics of a Non-Slender Lambda Wing Unmanned Aerial Vehicle

Numerical Investigation of Flow Characteristics of a Non-Slender Lambda Wing Unmanned Aerial Vehicle

Propeller locations study of a generic delta wing UAV model

Effects of the Propeller Advance Ratio on Delta Wing UAV Leading Edge Vortex

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