Joukowski Airfoil — Conformal Mapping
Circle → airfoil via z + c²/z · Streamlines show lift generation
w(z) = U(z·e⁻ⁱᵅ + a²·eⁱᵅ/z) + Γ/(2πi)·ln(z) | L = ρUΓ (Kutta–Joukowski)
CL = 0.00 | Γ = 0.000
The Joukowski transform w = z + c²/z maps a circle to an airfoil shape.
Streamlines (left: circle plane, right: airfoil plane) reveal how circulation Γ creates lift.
The Kutta condition sets Γ so the rear stagnation point sits at the trailing edge.