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Research Papers: Flows in Complex Systems

Flow Physics of a Race Car Wing With Vortex Generators in Ground Effect

[+] Author and Article Information
Yuichi Kuya

School of Engineering Sciences, University of Southampton, Southampton, Hampshire SO17 1BJ, UKyuichi@soton.ac.uk

Kenji Takeda

School of Engineering Sciences, University of Southampton, Southampton, Hampshire SO17 1BJ, UKktakeda@soton.ac.uk

Xin Zhang

School of Engineering Sciences, University of Southampton, Southampton, Hampshire SO17 1BJ, UKx.zhang1@soton.ac.uk

Scott Beeton1

School of Engineering Sciences, University of Southampton, Southampton, Hampshire SO17 1BJ, UK

Ted Pandaleon2

School of Engineering Sciences, University of Southampton, Southampton, Hampshire SO17 1BJ, UK

1

Present address: Williams F1.

2

Present address: TotalSim LLC.

J. Fluids Eng 131(12), 121103 (Nov 19, 2009) (9 pages) doi:10.1115/1.4000423 History: Received March 20, 2009; Revised October 01, 2009; Published November 19, 2009; Online November 19, 2009

This paper experimentally investigates the use of vortex generators for separation control on an inverted wing in ground effect using off-surface flow measurements and surface flow visualization. A typical racing car wing geometry is tested in a rolling road wind tunnel over a wide range of incidences and ride heights. Rectangular vane type of sub-boundary layer and large-scale vortex generators are attached to the suction surface, comprising counter-rotating and corotating configurations. The effects of both device height and spacing are examined. The counter-rotating sub-boundary layer vortex generators and counter-rotating large-scale vortex generators suppress the flow separation at the center of each device pair, while the counter-rotating large-scale vortex generators induce horseshoe vortices between each device where the flow is separated. The corotating sub-boundary layer vortex generators tested here show little evidence of separation control. Increasing the spacing of the counter-rotating sublayer vortex generator induces significant horseshoe vortices, comparable to those seen in the counter-rotating large-scale vortex generator case. Wake surveys show significant spanwise variance behind the wing equipped with the counter-rotating large-scale vortex generators, while the counter-rotating sub-boundary layer vortex generator configuration shows a relatively small variance in the spanwise direction. The flow characteristics revealed here suggest that counter-rotating sub-boundary layer vortex generators can provide effective separation control for race car wings in ground effect.

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Copyright © 2009 by American Society of Mechanical Engineers
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Figures

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Figure 1

Schematic of single-element wing, end plate, and VG

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Figure 2

Configurations of VGs on wing and laser sheet positions in PIV measurement: (a) counter-rotating VGs and (b) co-rotating VGs. Flow is from bottom to top.

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Figure 3

Surface flow visualization on suction surface around centre portion of wing span at α=1 deg and (h/c)=0.090: (a) clean, (b) CtSVG, (c) CtLVG, and (d) CoSVG. Flow is from bottom to top.

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Figure 4

Surface flow visualization on suction surface around centre portion of wing span for effect of VG device spacing at α=1 deg and (h/c)=0.090: (a) close-spacing and (b) wide-spacing. Flow is from bottom to top.

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Figure 5

Mean streamwise velocity contours at α=1 deg and (h/c)=0.090: (a) clean, (b) CtSVG at z=za and zb, (c) CtLVG at z=za and zb, and (d) CoSVG at z=zc

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Figure 6

Mean streamwise velocity profiles at (x/c)=1.5 at α=1 deg and (h/c)=0.090

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Figure 8

Mean spanwise vorticity distributions at α=1 deg and (h/c)=0.090: (a) clean, (b) CtSVG at z=za and zb, (c) CtLVG at z=za and zb, and (d) CoSVG at z=zc

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Figure 7

Instantaneous spanwise vorticity distributions at α=1 deg and (h/c)=0.090: (a) clean, (b) CtSVG at z=za and zb, (c) CtLVG at z=za and zb, and (d) CoSVG at z=zc

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