Reverie Universal Fit Motorsport Dual Element 225mm + 110mm Chord Rear Wing Data

Designed by Aerodynamics writer and designer Simon McBeath (author of Competition Car Aerodynamics) for ReVerie using Fluent Flowizard software. Data and images generated by the CFD software are displayed below.
The wing profile was designed to give a range of downforce levels from moderate to reasonably high, depending on deployed angle of attack and chosen span.

SPECIFICATION

Two universal fit designs are available, either a straight design or a curved design with a 1600mm radius. The wings feature internal longitudinal stringers along the length and end spars with 2 x M6 threaded inserts for mounting between supports or for affixing end plates.
On single element 225mm & 150 mm wings the end plate ‘notch’ was incorporated to increase the wing’s efficiency by beneficially modifying the airflow around the wing tips’. The wings come ready to mount between supports on the end spars or can be supplied with underside double or single shear carbon fibre mounting plates.

ORDERING INFORMATION

Specify straight or curved profile and required span width when ordering. The wing comes supplied with support tabs, rivets and adhesive for post or pillar mounting. Alternatively the end plates can be removed & the wing mounted between wing uprights. Also specify any special end-mount fixing details when ordering.

You may also like to order the optional 5mm or 10mm high gurney flaps. These can improve the lift / drag performance and reduce the onset of stall at higher angles of attack. These can be bonded on with adhesive or in some cases a high strength double-sided tape with suitable surface preparation. These can be purchased at a later date if required. Replacement end plates are also available separately.

RESULTS

(Based on a generic wing with ReVerie profile)
Forces on Wing at Different Angles & Spans
Single Element
Calculated forces at different spans and angles, taking into account efficiencies at different spans
Air speed 44.7m/s (100mph)

Tuning Advice

The recommended maximum angle of attack with this wing in free stream air is 20^O, although this may be different when mounted on a car.
Forces increase with span width as per tables above The rise in the forces at speed are in line with the square of the velocity increase. Thus, to calculate forces at different speeds within the range bracketed here simply multiply by the square of the ratio of the speeds in question. Below 100mph some caution should be used when applying this square law, but approximations of forces down to perhaps 60mph or 70mph will be valid.

To Scale a force to a different speed.

We will use the Notched end plate design figure at 100MPH from above. Then scale it to 150MPH.

New Force (N) = Original Force (N) x (New Speed² (MPH) ÷ Data Speed² (MPH))
New Force = 937.2 x ((150 x 150) ÷ (100 x 100))
New Force = 937.2 x 2.25
New Force = 2108.7

A 5 or 10mm Gurney flap could be added to the rear flap to further add a reasonably efficient increment of down force. All the results obtained were from evaluations in free stream air, with horizontal onset flow to the wing. is obviously not representative of the onset flow on the back of a car. Nevertheless, the generic findings of this project should be valid Pressure distribution along the wing centreline Pressure distribution along the wing centreline Velocity vectors, coloured by static pressure, along the wing centreline over upper & lower surfaces of the wing.