04 / Engineering workbench

AeroLab

Change a wing shape and watch a fast estimate respond.

Live browser preview · low-order model

Interactive / low-order preview

Change the airfoil

NACA four-digit profileAngle of attack 6°Air speed 28 m/s

Model and assumptions

NACA four-digit geometry uses a standard thickness and camber equation. The estimates use thin-airfoil slope, finite-wing correction, an empirical stall decay, and induced plus baseline drag. Fixed wing: 1 m chord, 8 m² area, aspect ratio 8; sea level at 15°C. This is a port of AeroLab’s preview equations, not a validated CFD result.

Lift coefficient—

Drag coefficient—

Lift estimate—

Stall margin—

Values update from the selected shape, angle, and air speed.

Reading the estimate

Shape

A four-digit NACA code sets airfoil camber and thickness. Angle rotates the section through the flow.

Curve

The lift curve below shows the preview model from −10° to 20°. The marker follows your chosen angle.

Units

Lift coefficient and drag coefficient are dimensionless. Lift force uses the fixed 8 m² wing and the selected air speed.

Lift across angles

NACA 2412 · 6° · lift coefficient

The curve uses the same low-order preview equation as the numbers above. The marker follows your selected angle; the model is intended for exploration.

AeroLab is a Python-first aerodynamic workbench for early airfoil and wing exploration. The browser preview ports its NACA four-digit geometry and low-order lift and drag equations.

Move the angle and speed controls to see the section, lift curve, and force estimate change together. The local workbench also has panel, viscous-panel, lattice Boltzmann, and external solver paths.