The NACA 6-Series airfoil profile is automatically generated according to the series designation (63, 64, 65, etc.), the ideal lift coefficient, and the thickness to chord ratio and the functions that specify the airfoil shape. The airfoil name will also automatically be altered as these parameters are changed according to convention. The “6A” series airfoils also fall into this category. This series aims to alleviate the sharp trailing edge cusp that is present in normal 6-series airfoils. Note that you also have the A value which indicates the fraction of the chord with laminar flow over the airfoil, set to 100% or 1.0 by default.