✈️ Bernoulli's Principle — Airfoil Lift & Flow

Explore how Bernoulli's equation P + ½ρv² = const governs airfoil aerodynamics. Watch streamlines around a NACA-style wing, see the pressure colour map, and discover how angle of attack generates lift — until the wing stalls.

Angle of attack α: 5°

Flow speed U: 60 m/s

Thickness t/c: 12%

C_L: —

C_D: —

L/D: —

Lift: — N/m

ΔP: — Pa

⚠ STALL

Physics

Bernoulli's equation: P + ½ρv² = const along a streamline. Where the flow speeds up (above the wing), pressure drops; where it slows (below), pressure rises. This pressure difference creates lift.

Lift coefficient (thin airfoil theory): C_L = 2π·sin(α), valid up to the stall angle α ≈ 15–18°. Beyond that, flow separates and C_L drops abruptly. Lift per unit span: L = ½ρU²·C_L·c. Kutta-Joukowski: L = ρ·U·Γ where Γ is bound circulation.