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Research Papers: Fundamental Issues and Canonical Flows

The Wingtip Vortex of a Dimpled Wing With an Endplate

[+] Author and Article Information
Christopher C. Beves

School of Mechanical and Manufacturing Engineering,
University of New South Wales (UNSW),
Sydney 2052,
Australia;
CD-Adapco,
200 Shepherds Bush Road,
London W6 7NL, UK
e-mail: cbeves@gmail.com

Tracie J. Barber

School of Mechanical and Manufacturing Engineering,
University of New South Wales (UNSW),
Sydney 2052, Australia
e-mail: t.barber@unsw.edu.au

Contributed by the Fluids Engineering Division of ASME for publication in the JOURNAL OF FLUIDS ENGINEERING. Manuscript received December 31, 2015; final manuscript received August 18, 2016; published online November 3, 2016. Editor: Malcolm J. Andrews.

J. Fluids Eng 139(2), 021202 (Nov 03, 2016) (9 pages) Paper No: FE-15-1966; doi: 10.1115/1.4034525 History: Received December 31, 2015; Revised August 18, 2016

Dimples used as sub-boundary layer vortex generators have been shown to reduce wake size at large angles of incidence. The effect these dimples have on wingtip vortices with an endplate is measured via laser Doppler anemometry (LDA) on an inverted Tyrrell026 airfoil (ReC = 0.5 × 105 and chord = 0.075 m) in ground effect in order to determine the flow characteristics for this configuration and to see if previous measurements were performed in a thinner part of the wake due to any potential wake waviness. The strength of the wingtip vortex for the dimpled wing is 10% higher than the “clean” wing immediately downstream. The clean wing has large region of high turbulence throughout the wake, and the dimples reduce this by 50%. The net result is that dimples drastically improve the flow in the wake of the wing and endplate.

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References

Figures

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Fig. 1

(a) UNSW laser diagnostic wind tunnel and (b) test section detail

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Fig. 2

(a) Test section and wing position layout and (b) LDA grid

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Fig. 3

Wingtip experimental setup: (a) endplate and (b) measurement planes

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Fig. 4

Normalized streamwise velocity at x/c = 1.27: (a) clean and (b) 1.5-3-23 and x/c = 2.07: (c) clean and (d) 1.5-3-23

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Fig. 5

Wake pathlines at x/c = 1.27: (a) clean and (b) 1.5-3-23 and x/c = 2.07: (c) clean and (d) 1.5-3-23

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Fig. 6

Normalized X-vorticity at x/c = 1.27: (a) clean and (b) 1.5-3-23 and x/c = 2.07: (c) clean and (d) 1.5-3-23

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Fig. 7

Normalized turbulent kinetic energy at x/c = 1.27: (a) clean and (b) 1.5-3-23 and x/c = 2.07: (c) clean and (d) 1.5-3-23

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Fig. 8

Normalized turbulent normal stress at x/c = 1.27: (a) clean and (b) 1.5-3-23 and x/c = 2.07: (c) clean and (d) 1.5-3-23

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