✈️ 2D Bernoulli's Principle — Airfoil Lift & Pressure Map

A NACA-style symmetric wing sits in a uniform 2D airstream. Bernoulli's equation P + ½ρv² = const links local speed to local pressure; a circulation model bends the streamlines and a heat-map shades low pressure blue, high pressure red — the difference that produces lift.

Wing

Angle of attack α 5.0° Flow speed U 60 m/s Thickness t/c 12% Air density ρ 1.225 kg/m³

Results

C_L—

C_D—

L/D—

Lift—

ΔP—

Dyn. press. q—

Presets

How it works

The wing is a symmetric NACA-profile section — thickness only, no camber — so angle of attack alone controls how fast the flow passes above versus below. Bernoulli's equation P + ½ρv² = const then converts that speed difference into a pressure difference: faster flow above the wing means lower pressure there, slower flow below means higher pressure, and the net upward force is lift.

Lift coefficient follows thin-airfoil theory, C_L = 2π·sin(α), valid up to the stall angle (≈15°); beyond that the model switches to a decaying curve that mimics flow separation, exactly like the 3D version of this simulation — but every pixel here, including the pressure heat-map, is computed and painted on a plain 2D canvas with no WebGL involved.