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The equations for the NACA 4-digit and 4-digitmodified sections are in algebraic form and easily incorporated into various geometrical procedures that define a vehicle and any necessary flow field grid. The 6-series and 6A-series airfoils are more complex because they are developed by conformal mapping procedures. Even though there are computer programs available (refs 1-3) that can produce a large table of points on the surface of the airfoil, there is a frequently expressed desire for an algorithm that will calculate the upper and lower ordinates and slopes of a cambered airfoil at a specified chord location that requires no interpolation on the part of the user. The purpose of this paper is to present such an algorithm and describe subroutines that may be used for these calculations. A public domain computer program incorporating these procedures has been written and may be downloaded from the author's web site. This program is modular, allowing its internal procedures to be used in other programs.

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