Airfoil Profile

NACA1411 'AirfoilProfile' inspector

ScriptableObject defining airfoil behavior.

Fields

  • 2D Cross-section - Airfoil profile icon (Y exaggerated).

  • Coefficients - Cl (Lift Coefficient), Cd (Drag Coefficient), and Cm (Moment Coefficient) base values affecting all airfoils using this profile. For per-airfoil adjustment, see Airfoil inspector.

  • Curves - Lift/drag/moment vs angle of attack (X: [-90, 90]). Parsed from polar string data or set manually.

  • Parsing - Converts polar data (e.g., from XFOIL) to curves. Header Lines specifies initial lines to ignore (12 for XFOIL format), index values define column order.

Included Airfoil Profiles

1000+ common airfoils included. NACA airfoils are located in NWH > Aerodynamics > Scripts > Airfoil > AirfoilProfiles. Import additional airfoil profiles via the AirfoilProfiles.unitypackage file.