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Research Papers: Flows in Complex Systems

Flow Separation Control on a Race Car Wing With Vortex Generators in Ground Effect

[+] Author and Article Information
Yuichi Kuya

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

Kenji Takeda

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

Xin Zhang

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

Scott Beeton1

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

Ted Pandaleon2

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

1

Present address: Williams F1.

2

Present address: TotalSim LLC.

J. Fluids Eng 131(12), 121102 (Nov 19, 2009) (8 pages) doi:10.1115/1.4000420 History: Received March 20, 2009; Revised October 01, 2009; Published November 19, 2009; Online November 19, 2009

Flow separation control using vortex generators on an inverted wing in ground effect is experimentally investigated, and its performance is characterized in terms of forces and pressure distributions over a range of incidence and ride height. Counter-rotating and co-rotating rectangular-vane type vortex generators are tested on the suction surface of the wing. The effect of device height and spacing is investigated. The counter-rotating sub-boundary layer vortex generators and counter-rotating large-scale vortex generators on the wing deliver 23% and 10% improvements in the maximum downforce, respectively, compared with the clean wing, at an incidence of one degree, and delay the onset of the downforce reduction phenomenon. The counter-rotating sub-boundary layer vortex generators exhibit up to 26% improvement in downforce and 10% improvement in aerodynamic efficiency at low ride heights. Chordwise pressure measurement confirms that both counter-rotating vortex generator configurations suppress flow separation, while the co-rotating vortex generators exhibit negligible effectiveness. This work shows that a use of vortex generators, notably of the counter-rotating sub-boundary layer vortex generator type, can be effective at controlling flow separation, with a resultant improvement in downforce for relatively low drag penalty.

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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

Configuration of VGs on wing: (a) counter-rotating VGs and (b) co-rotating VGs. Flow is from bottom to top.

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Figure 3

Force characteristics at various ride heights at α=1 deg: (a) downforce and (b) drag

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Figure 4

Downforce characteristics with respect to incidence and ride height: (a) clean, (b) CtSVG, (c) CtLVG, and (d) CoSVG

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Figure 5

Effect of counter-rotating VGs on downforce and downforce-to-drag ratio improvements relative to clean wing: (a) CtSVG and (b) CtLVG

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Figure 6

Effect of VG device spacing on downforce and downforce-to-drag ratio improvements relative to clean wing: (a) close-spacing CtSVG and (b) wide-spacing CtSVG

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Figure 7

Averaged-chordwise surface pressure distributions on wing at α=1 deg and (h/c)=0.090

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Figure 8

Schematic of pressure tapped array and mirrored pressure tapped array of counter-rotating VG configuration

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Figure 9

Schematic of pressure tapped array and mirrored pressure tapped array of co-rotating VG configuration

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