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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.

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References

Morton, S. , Forsythe, J. , Mitchell, A. , and Hajek, D. , 2002, “ Detached-Eddy Simulations and Reynolds-Averaged Navier–Stokes Simulations of Delta Wing Vortical Flowfields,” ASME J. Fluids Eng., 24(4), pp. 924–932. [CrossRef]
Wang, F. Y. , Milanovic, I. M. , Zaman, K. B. , and Povinelli, L. A. , 2005, “ A Quantitative Comparison of Delta Wing Vortices in the Near-Wake for Incompressible and Supersonic Free Streams,” ASME J. Fluids Eng., 127(6), pp. 1071–1084. [CrossRef]
Liu, T. , Makhmalbaf, M. M. , Vewen Ramasamy, R. , Kode, S. S. , and Merati, P. P. , 2015, “ Skin Friction Fields and Surface Dye Patterns on Delta Wings in Water Flows,” ASME J. Fluids Eng., 137(7), pp. 202–214. [CrossRef]
Lowson, M. V. , and Riley, A. J. , 1995, “ Vortex Breakdown Control by Delta Wing Geometry,” J. Aircr., 32(4), pp. 832–838. [CrossRef]
Nelson, R. C. , and Pelletier, A. , 2003, “ The Unsteady Aerodynamics of Slender Wings and Aircraft Undergoing Large Amplitude Maneuvers,” Prog. Aerosp. Sci., 39(2–3), pp. 185–248. [CrossRef]
Gursul, I. , Wang, Z. , and Vardaki, E. , 2007, “ Review of Flow Control Mechanisms of Leading-Edge Vortices,” Prog. Aerosp. Sci., 43(7–8), pp. 246–270. [CrossRef]
Gerhardt, H. A. , 1996, “ Supersonic Natural Laminar Flow Wing,” U.S. Patent No. 5,538,201.
Altaf, A. , Omar, A. A. , Asrar, W. , and Jamaluddin, H. B. L. , 2011, “ Study of the Reverse Delta Wing,” J. Aircr., 48(1), pp. 277–286. [CrossRef]
Rozhdestven, K. V. , 2006, “ Wing-in-Ground Effect Vehicles,” Prog. Aerosp. Sci., 42(3), pp. 211–283. [CrossRef]
Lee, T. , and Su, Y. Y. , 2012, “ Wingtip Vortex Control Via the Use of a Reverse Half-Delta Wing,” Exp. Fluids, 52(6), pp. 1593–1609. [CrossRef]
Lee, T. , and Choi, S. , 2015, “ Wingtip Vortex Control Via Tip-Mounted Half-Delta Wings of Different Geometric Configurations,” ASME J. Fluids Eng., 137, pp. 1–9.
Zhan, J. X. , and Wang, J. J. , 2004, “ Experimental Study on Gurney Flap and Apex Flap on a Delta Wing,” J. Aircr., 41(6), pp. 1379–1383. [CrossRef]
Wang, J. J. , Li, Y. C. , and Choi, K.-S. , 2008, “ Gurney Flap—Lift Enhancement, Mechanisms and Applications,” Prog. Aerosp. Sci., 44(1), pp. 22–47. [CrossRef]
Payne, F. M. , Ng, T. T. , and Nelson, R. C. , 1989, “ Seven Hole Probe Measurement of Leading Edge Vortex Flows,” Exp. Fluids, 7(1), pp. 1–8. [CrossRef]
Wu, H. , Miorini, R. L. , Tan, D. , and Katz, J. , 2012, “ Turbulence Within the Tip-Leakage Vortex of an Axial Waterjet Pump,” AIAA J., 50(11), pp. 2574–2587. [CrossRef]
Kaplan, S. M. , Altman, A. , and Ol, M. , 2007, “ Wake Vorticity Measurements for Low Aspect Ratio Wings at Low Reynolds Number,” J. Aircr., 44(1), pp. 241–251. [CrossRef]

Figures

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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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