• 2D Cross-section - an icon of the 2D cross-section of the airfoil. Note that the Y dimension is exaggerated to better show the shape of the airfoil.

• Coefficients - Cl (coefficient of lift), Cd (coefficient of drag) and Cm (coefficient of moment) can be used to tune the base behavior of the AirfoilProfile. These fields affect all the Airfoils using this AirfoilProfile. For individual coefficient adjustment check the Airfoil inspector.

• Curves - AnimationCurves representing the lift, drag and moment values along the Y axis against the angle of attack on the X axis. X axis should be in range of [-90, 90]. Usually parsed from the Polar String but can also be set manually.

• Parsing - Converts polar data from 2D airfoil simulation software such as XFoil into curves. Header Lines determines the number of initial lines to ignore (11 for XFoil) and the index values determine which column is what. By default the first column determines the angle of attack, next column is coefficient of lift, etc. If the curves are set manually this section can be ignored.

Over 1000 common airfoils are included.

After importing only NACA airfoils will be present in the NWH > Aerodynamics > Scripts > Airfoil > AirfoilProfiles directory but by double clicking on AirfoilProfiles.unitypackage in NWH > Aerodynamics > Scripts > Airfoil the rest of the AirfoilProfiles will get imported.