Airfoil Parameters
Quick Generation
NACA
Examples: 0012 2412 4415
Parameter format
C P TT
Current NACA: NACA 0012
Or specify exact parameters:
Length from leading to trailing edge Range: ≥ 0.1
Chord Length
fraction of chord
Thickness at the thickest point Range: 0.01 - 0.2
Maximum Thickness
fraction of chord
Maximum curvature of the mean line Range: 0 - 0.1
Maximum Camber
fraction of chord
Position of maximum camber Range: 0.001 - 0.999
Camber Position
Generated Airfoil
Generated Airfoil
Aerodynamic Performance
Key Metrics
Visualized Performance

Detailed performance visualizations can be viewed using the buttons below. These show lift and drag characteristics at various angles of attack.

Technical calculations based on thin airfoil theory with corrections for thickness, camber, and Reynolds number effects.
AI Suggestions
Saved Designs
No Saved Designs

No airfoil designs have been saved yet.

Create New Design
AeroFoil Assistant
Powered by Gemini AI
AeroFoil Assistant
Powered by Gemini AI

👋 Hi there! I'm your AeroFoil Assistant. I can help with airfoil design questions, from basic concepts to technical details.

Try asking me something like "What's an airfoil?" or "How do camber and thickness affect performance?"

What's an airfoil? How do airfoils generate lift? What's a NACA profile? Symmetric vs asymmetric airfoils?