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Maximum thickness is 12% of the chord (located at 30% of the chord).Maximum camber located at 40% of the chord.Maximum thickness occurs at 30% of the chord.All digits are a percentage of the chord length.The 3rd and 4th digits represent the maximum thickness.The 2nd digit is the maximum camber location.Airfoils can be generated with either sharp or blunt trailing edges. Simply input the 4 digits defining a NACA 4-Series airfoil and click CREATE. This script provides a way to generate NACA 4-Series airfoil geometries within Pointwise without relying on external coordinate files. All rights reserved worldwide.Ī Glyph script for generating NACA 4-series airfoil geometries. Copyright 2021 Cadence Design Systems, Inc.