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

How it works

A symmetric NACA-profile wing — thickness only, no camber — sits in a uniform 2D airstream. Tilting it to a non-zero angle of attack makes the flow speed up over the upper surface and slow down underneath; Bernoulli's equation P + ½ρv² = const converts that speed split directly into a pressure split, and the pressure difference summed over the whole chord is lift.

Lift coefficient follows thin-airfoil theory, C_L = 2π·sin(α), up to the modelled stall angle near 15°, after which the curve decays to mimic flow separation — the same physics as the 3D version of this page, reproduced here with a plain 2D canvas pressure heat-map instead of a WebGL shader, plus an independent air-density control so you can see how thin the Martian atmosphere makes lift compared to sea level on Earth.