Flow reattachment – improved aerodynamic downforce

α ≈ 0

CL ≈ y

Normal angled wing

α ≈ x

CL ≈ 2 y

Increased angle of attack

α ≈ 2 x

CL ≈ 0,5 y

Separated airfoil

α ≈ 2 x

CL ≈ 3 y

Increased CL with Vortaflow

α ≈ 0 CL ≈ yα ≈ x CL ≈ 2 y

α ≈ 2 x CL ≈ 0,5 y

α ≈ 2 x CL ≈ 3 y

Current technology With Vortaflow

Reynolds number ≈ 2 · 106

Current technology With Vortaflow

Reynolds number ≈ 2 · 106

Tests on a Porsche 996 GT3 RS

Result: 5% increase in

cornering speed

Design progress:

Equations

Experiments

Experience