Research Papers: Flows in Complex Systems

Impact of Gurney Flaplike Strips on the Aerodynamic and Vortex Flow Characteristic of a Reverse Delta Wing

[+] Author and Article Information
T. Lee

Department of Mechanical Engineering,
McGill University,
Montreal, QC H3A 2K6, Canada

Contributed by the Fluids Engineering Division of ASME for publication in the JOURNAL OF FLUIDS ENGINEERING. Manuscript received June 20, 2015; final manuscript received November 9, 2015; published online February 18, 2016. Assoc. Editor: Feng Liu.

J. Fluids Eng 138(6), 061104 (Feb 18, 2016) (9 pages) Paper No: FE-15-1413; doi: 10.1115/1.4032301 History: Received June 20, 2015; Revised November 09, 2015

The impact of Gurney flaplike strips, of different geometric configurations and heights, on the aerodynamic characteristics and the tip vortices generated by a reverse delta wing (RDW) was investigated via force-balance measurement and particle image velocimetry (PIV). The addition of side-edge strips (SESs) caused a leftward shift of the lift curve, resembling a conventional trailing-edge flap. The large lift increment overwhelmed the corresponding drag increase, thereby leading to an improved lift-to-drag ratio compared to the baseline wing. The lift and drag coefficients were also found to increase with the strip height. The SES-equipped wing also produced a strengthened vortex compared to its baseline wing counterpart. The leading-edge strips (LESs) were, however, found to persistently produce a greatly diffused vortex flow as well as a small-than-baseline-wing lift in the prestall α regime. The downward LES delivered a delayed stall and an increased maximum lift coefficient compared to the baseline wing. The LESs provide a potential wingtip vortex control alternative, while the SESs can enhance the aerodynamic performance of the RDW.

Copyright © 2016 by ASME
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Fig. 1

Schematics of (a) PIV setup and (b) wing models

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Fig. 2

Impact of SES and LES on RDW aerodynamic characteristics at Re = 4.06 × 105. RDW and DW denote reverse delta wing and regular delta wing, respectively.

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Fig. 3

Photos of visualized baseline RDW flow patterns at α = 14 deg and 24 deg. The flow is from right to left. Smoke-wire flow visualization: (a) α = 14 deg and (b) α = 24 deg. Dye-injection flow visualization: (c) α = 14 deg and (d) α = 24 deg. SVF denotes spanwise vortex filament.

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Fig. 4

Normalized iso-axial velocity contours at x/c = 1.01 for α = 16 deg

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Fig. 5

Combined spatial progression of normalized isovorticity contours at α = 16 deg. (a) BW and SES wing, (b) BW and LESd wing, and (c) BW and LESu wing. BW denotes baseline RDW.

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Fig. 6

Variation of vortex flow parameters with x/c at α = 16 deg

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Fig. 7

Normalized tangential velocity across the vortex center at x/c = 1.5 for α = 16 deg

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Fig. 8

CLα curves at Re = 1.1 × 104. DW denotes regular delta wing.

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Fig. 9

Variation of vortex flow parameters with α at x/c = 1.01

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Fig. 10

Normalized isovorticity contours at x/c = 1.01 for selected α




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