Oscillations of Leading-Edge Vortex Breakdown Locations over a Delta Wing

AIAA Journal ◽  
2018 ◽  
Vol 56 (6) ◽  
pp. 2113-2118
Author(s):  
Lu Shen ◽  
Chih-yung Wen
Keyword(s):  
Vortex Breakdown ◽  
Delta Wing ◽  
Leading Edge ◽  
Leading Edge Vortex ◽  
Edge Vortex

scholarly journals The Leading-Edge Vortex of Swift Wings

2017 ◽  
Author(s):  
Rowan Eveline Muir ◽  
Ignazio Maria Viola
Keyword(s):  
Vortex Breakdown ◽  
Delta Wing ◽  
Leading Edge ◽  
Leading Edge Vortex ◽  
Wing Model ◽  
Image Velocimetry ◽  
Edge Vortex ◽  
First Time ◽  
Swept Wings ◽  
Sharp Leading Edge

1AbstractRecent 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 will serve to add understanding to the complex aerodynamics of natural fliers. In this investigation, the wing of a common swift Apus apus is simplified to a model with swept wings and a sharp leading-edge, making it readily comparable to a model delta shaped wing of the same leading-edge geometry. Particle image velocimetry provides an understanding of the effect of the tapering swift wing on LEV development and stability, compared with the delta wing model. For the first time a dual LEV is recorded on a swift shaped wing, where it is found across all tested conditions. It is shown that the span-wise location of LEV breakdown is governed by the local chord rather than Reynolds number or angle of attack. These findings suggest that the common swift is able to generate a dual LEV while gliding, potentially delaying vortex breakdown by exploiting other features non explored here, such as wing twist and flexibility. It is further suggested that the vortex system could be used to damp loading fluctuations, reducing energy expenditure, rather than for lift augmentation.

Parametric Investigations of the Leading Edge Vortex on a Delta Wing

2011 ◽  
Author(s):  
Christoph Strangfeld ◽  
Lutz Taubert ◽  
C. Nayeri ◽  
Christian Paschereit
Keyword(s):  
Delta Wing ◽  
Leading Edge ◽  
Leading Edge Vortex ◽  
Edge Vortex

Control of Leading-Edge Vortex Breakdown by Trailing Edge Injection

2002 ◽  
Vol 39 (2) ◽  
pp. 221-226 ◽  
Author(s):  
Anthony M. Mitchell ◽  
Didier Barberis ◽  
Pascal Molton ◽  
Jean Delery
Keyword(s):  
Vortex Breakdown ◽  
Leading Edge ◽  
Trailing Edge ◽  
Leading Edge Vortex ◽  
Edge Vortex

Leading-edge vortex behavior in the vicinity of delta wing apex

1996 ◽  
Author(s):  
Gregory Addington ◽  
Ernest Hanff ◽  
Robert Nelson
Keyword(s):  
Delta Wing ◽  
Leading Edge ◽  
Leading Edge Vortex ◽  
Edge Vortex

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

2019 ◽  
Vol 16 (3) ◽  
pp. 6958-6970 ◽  
Author(s):  
K. A. Kasim ◽  
P. Segard ◽  
S. Mat ◽  
S. Mansor ◽  
M. N. Dahalan ◽  
...  
Keyword(s):  
Swirling Flow ◽  
Delta Wing ◽  
Active Flow Control ◽  
Pressure Coefficient ◽  
Leading Edge ◽  
Adverse Pressure Gradient ◽  
Leading Edge Vortex ◽  
Wing Model ◽  
Edge Vortex ◽  
Advance Ratio

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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