top of page
FSAE
FRONT
WING
STUDY
A data-driven aerodynamic study optimising gap and overlap in a two-element FSAE front-wing section.
THE PROBLEM
Identifying the gap and overlap configuration that maximises aerodynamic performance within the investigated 2D design space.
Overlap
Gap
Airfoil:
S1223
Main Plane
Chord: 300mm
AoA: 5°Â
Flap
Chord: 150mm
AoA: 20°Â
OPTIMAL DESIGN
Gap:
15mm
5% Chord
Overlap:
3mm
1% Chord
Downforce:
133.7N
Aerodynamic Efficiency:
6.20
DESIGN SPACE
DESIGN SPACE
Gap:
3mm - 15mm
Overlap:
3mm - 15mm
30
Design Points
CFD METHODLOGY
Wake Refinement:
6mm
Solver:
ANSYS Fluent
Turbulence Model:
k-ω SST
Body Refinement:
3mm
Convergence Criteria
Lift, Drag, Residuals
Inflation Layers:
0.3 < y+ < 1.4
RESPONSE SURFACE
Polynomial regression models were fitted to the CFD data to predict mainplane and flap lift and drag across a dense gap–overlap grid, generating continuous response surfaces from the 30 CFD samples.
The response surfaces identified high gap and low overlap as favourable for downforce, with gap driving the associated drag increase.
PARETO OPTIMISATION
Pareto analysis identified the non-dominated trade-off between downforce and drag.
The highest downforce configuration along the Pareto front was selected.
UNDERSTANDING THE FLOW
Â
The velocity contour below highlights the key flow features driving DP29’s aerodynamic performance.
Strong acceleration beneath the mainplane generates the majority of the aerodynamic loading, while the inter-element slot directs higher-energy flow toward the flap, supporting flow attachment and allowing the downstream element to generate additional downforce.
CONCLUSION
Â
Within the design space studied, 5% gap and 1% overlap, relative to the mainplane chord, produced the best overall aerodynamic performance, with gap having the strongest influence on drag.
MOVING FORWARD
Â
This 2D study establishes a baseline element configuration rather than a final front-wing design. The selected gap and overlap will now be used as the starting point for developing the 3D front-wing profiles, where spanwise geometry, local angle of attack, loading distribution, endplate effects, and wheel-wake management can be investigated.
bottom of page