A Glyph script for generating NACA 4-series airfoil geometries.

This script provides a way to generate NACA 4-Series airfoil geometries within Pointwise without relying on external coordinate files. Simply input the 4 digits defining a NACA 4-Series airfoil and click CREATE. Airfoils can be generated with either sharp or blunt trailing edges.

• The 1st digit is the maximum camber
• The 2nd digit is the maximum camber location
• The 3rd and 4th digits represent the maximum thickness

• All digits are a percentage of the chord length
• Maximum thickness occurs at 30% of the chord
• Chord length fixed to a unit length

• Maximum camber is 2% of the chord
• Maximum camber located at 40% of the chord
• Maximum thickness is 12% of the chord (located at 30% of the chord)

Scripts are freely provided. They are not supported products of Pointwise, Inc. Some scripts have been written and contributed by third parties outside of Pointwise's control.

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