WindLab Pro Airfoil Laboratory

Airfoil Laboratory

Analyze NACA 4-digit or uploaded Selig DAT airfoils with a fast transparent screening model or run the real XFOIL 6.996 solver directly in the browser through WebAssembly—no external backend required.

Solver modeBrowser screening

Airfoil definition

Source

NACA code

Enter any valid NACA four-digit code.

Flow conditions

Reynolds number

Mach number

α min (°)

α max (°)

Δα (°)

Model controls

Transition Ncrit

XFOIL iterations

Panels

Cp angle (°)

Apply roughness / early-transition penalty in browser mode

XFOIL WebAssemblyLoads on demand

The original XFOIL 6.996 numerical engine is downloaded as a ~1 MB WebAssembly module when this mode is first used. Calculations then run locally in your browser.

Requires internet access on first load. The package is GPL-2.0-or-later; source and license information are included in the project notices.

Ready. Browser model mode is fully static and works on Cloudflare Pages.

CL max

—

CD min

—

Best CL/CD

—

Zero-lift α

—

interpolated

Airfoil geometry

Normalized chord coordinates.

Pressure coefficient

Selected angle of attack.

Lift, drag and moment

Polar coefficients versus angle of attack.

Aerodynamic efficiency

CL/CD and drag polar.

Polar table

Use native XFOIL mode for publication-grade converged values.