Control of Multiple Vortices over a Double Delta Wing

Xi, Zhang; Wang, Zhijin; Gursul, Ismet

doi:10.2514/6.2017-4122

Cited by 4 publications

(4 citation statements)

References 26 publications

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“…Since the main objective of this project was to determine the propeller effects on the leading-edge vortex, the model had been designed with the sharp-edged and tailless platform. A tailless platform delta wing was chosen to prevent the formation of multiple vortices over the wing [19]. The inner portion of the wing also was a flat plate in order to prevent the flow from becoming more complicated.…”

Section: Methodsmentioning

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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Section: Methodsmentioning

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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“…Passive bleed exploiting the natural pressure difference between the upper and lower surfaces can be an effective method to manipulate the tip/edge vortices. Bleed slots were placed near the wing tip/edge for rectangular wings [32], delta wings [33], and double-delta wings [34].…”

Section: Bleedmentioning

confidence: 99%

“…In the case of merging, this is promoted by the ingestion of the jet turbulence into the vortices. Vortex interactions can also be manipulated through passive bleed by exploiting the pressure difference between the upper and lower wing surfaces[34]. InFigure 16(c), for the same wing and measurement station, the effect of the spanwise location of the bleed hole at an upstream station is shown for two different cases (top yb/s = 0.10 and bottom 0.42).…”

mentioning

confidence: 99%

Flow Control of Tip/Edge Vortices

Gursul

Wang

2018

AIAA Journal

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Location, strength and structure of tip and edge vortices shed from wings and bodies can be manipulated by using flow control techniques. Flow physics of these approaches involve flow separation from the edge, roll-up into the vortex, wing flow regime, vortex instabilities, vortex-vortex interactions, and vortex-turbulence interactions. Actuators include continuous and unsteady blowing and suction, bleed, and control surfaces, which add momentum, vorticity and turbulence into the vortices. It is noted that actuation may have effects on more than one aspect of the flow phenomena. A comparative review of the control of delta wing vortices, tip vortices, and afterbody vortices is presented. The delay of vortex breakdown and the promotion of flow reattachment require different considerations for slender and nonslender delta wings, and may not be possible at all. Tip vortices can be controlled to increase the effective span, to generate rolling moment, to attenuate wing-rock, and to attenuate vortex-wing interactions. While there are different approaches for each application, opportunities for future research on turbulence ingestion, bleed, and excitation of vortex instabilities exist. Recent research also indicates that active and passive flow control can be used to manipulate the afterbody vortices in order to reduce the drag.

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“…The primary vortex on non-slender wing also develops closer to the wing surface and it is detached from the leading edge further downstream from the wing apex. There are several parameters that influenced that flow characteristics above the non-slender wing and one of them is wing swept angle (Brett and Ooi, 2014; Zhang et al , 2017). However, the flow characteristics above the slender wing exhibit differently.…”

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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Control of Multiple Vortices over a Double Delta Wing

Cited by 4 publications

References 26 publications

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

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

Flow Control of Tip/Edge Vortices

Propeller locations study of a generic delta wing UAV model

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