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 corotating 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.
|Number of pages||8|
|Journal||Journal of Fluids Engineering, Transactions of the ASME|
|Publication status||Published - 2009 Dec|
ASJC Scopus subject areas
- Mechanical Engineering