Flow over 50o Delta Wings with Different Leading-Edge Radii

Verhaagen, N.G.

doi:10.2514/6.2011-991

Cited by 9 publications

(4 citation statements)

References 18 publications

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“…Many (e.g. [16][17][18][19][20]) have experimentally and computationally explored non-slender delta wings of Λ = 50 • , with varying leadingedge radii and at a range of Re and α. These delta wings have a wing configuration comparable with that of the impressive natural fliers, the common swift Apus apus, when in non-diving, gliding flight.…”

Section: Introductionmentioning

confidence: 99%

The leading-edge vortex of swift wing-shaped delta wings

Muir¹,

Arredondo-Galeana²,

Viola³

2017

R. Soc. open sci.

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Recent investigations on the aerodynamics of natural fliers have illuminated the significance of the leading-edge vortex (LEV) for lift generation in a variety of flight conditions. A well-documented example of an LEV is that generated by aircraft with highly swept, delta-shaped wings. While the wing aerodynamics of a manoeuvring aircraft, a bird gliding and a bird in flapping flight vary significantly, it is believed that this existing knowledge can serve to add understanding to the complex aerodynamics of natural fliers. In this investigation, a model non-slender delta-shaped wing with a sharp leading edge is tested at low Reynolds number, along with a delta wing of the same design, but with a modified trailing edge inspired by the wing of a common swift Apus apus. The effect of the tapering swift wing on LEV development and stability is compared with the flow structure over the unmodified delta wing model through particle image velocimetry. For the first time, a leading-edge vortex system consisting of a dual or triple LEV is recorded on a swift wing-shaped delta wing, where such a system is found across all tested conditions. It is shown that the spanwise location of LEV breakdown is governed by the local chord rather than Reynolds number or angle of attack. These findings suggest that the trailing-edge geometry of the swift wing alone does not prevent the common swift from generating an LEV system comparable with that of a delta-shaped wing.

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Section: Introductionmentioning

confidence: 99%

The leading-edge vortex of swift wing-shaped delta wings

Muir¹,

Arredondo-Galeana²,

Viola³

2017

R. Soc. open sci.

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“…In general, the comparison shows that the Reynolds number has less effect on the coefficient of lift. This is because all the experiments were performed on sharp-edged wing which primary vortex formation is not dependent on the Reynolds number as explained by Verhaagen (2011).…”

Section: Steady Balance Datamentioning

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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“…Mass values have been estimated for Taranis and Neuron by estimating the payload based on similar configurations, as well as by averaging the payload and empty weight ratios of various demonstrators and concepts available in the literature. (Petterson, 2006;Tomac et al, 2010;Verhaagen, 2011). Computationally expensive CFD solvers are often employed in single design point studies; however this approach is not practical for large design space exploration studies at a conceptual design level.…”

Section: Mass Estimationmentioning

confidence: 99%

“…High fidelity studies concerning the aerodynamics of typical UCAV configurations have found complex flow topologies dominated by leading edge vortex interactions (Petterson, 2006;Tomac et al, 2010;Verhaagen, 2011). Computationally expensive CFD solvers are often used in single design point studies; however, this approach is not practical for large design space exploration studies at a conceptual design level.…”

Section: Aerodynamic Modellingmentioning

confidence: 99%

Impact of mission requirements on the design of low observable UCAV configurations

Palacios

Smith

2019

AEAT

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Purpose The purpose of this paper is to characterise the effects of mission and performance parameters on the design space of low observable subsonic unmanned combat aerial vehicles (UCAVs) operating in typical Hi-Lo-Hi ground strike missions. Design/methodology/approach Conceptual design methodologies appropriate to low observable, tailless UCAVs have been integrated into a multidisciplinary aircraft design environment, GENUS, developed at Cranfield University’s aircraft design group. A basic Hi-Lo-Hi mission is designed and a baseline configuration is established through the GENUS framework. Subsequently, an evolutionary optimiser and a robust gradient-based optimiser are used to obtain convergent design solutions for various leading edge sweep angles, mission ranges, cruise Mach numbers and other operational constraints. Findings The results indicate that performance constraints, specifically in the form of specific excess power (SEP), have a large influence on the overall sizing of subsonic tailless UCAVs. This requirement drives the engine sizing, which represents a considerable proportion of the empty and gross mass of the vehicle. Cruise Mach number studies show that no significant advantages exist for operating at low speeds while maintaining performance requirements consistent with combat missions. There is a drastic increase in the vehicle’s mass and thrust requirements for flight speeds above Mach 0.8, with low sweep configurations showing a more pronounced effect. Increases in the range are not overly dependent on the leading edge sweep angle. Top-level radar cross section (RCS) results also favour configurations with higher leading edge sweep angles, especially from the nose-on aspect. Finally, research and development costs are shown to be directly linked to engine size. Originality/value This research shows the use of an integrated aircraft design environment that incorporates aerodynamics, performance, packaging and low observability aspects into the optimisation loop. Through this methodology, this study supports the efforts towards characterising and establishing alternate visions of the future of aerial warfare through the use of low cost, survivable unmanned platforms in network-centric cooperative tasks.

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Flow over 50o Delta Wings with Different Leading-Edge Radii

Cited by 9 publications

References 18 publications

The leading-edge vortex of swift wing-shaped delta wings

The leading-edge vortex of swift wing-shaped delta wings

Propeller locations study of a generic delta wing UAV model

Impact of mission requirements on the design of low observable UCAV configurations

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