The thickness ordinates of most wing airfoil sections once normalized to their maximum thickness ordinates become quite similar between each other, and can be represented by some few functions as those presented in the tables and graphics of section 2, and Appendix I formulas.
It is shown that by combining these functions with different thickness with the uniform loading NACA a=1 mean line [1], airfoils for quite different applications, ranging from gliders [2], to high speed airplanes can be designed as exemplified by the six new airfoils presented with their main aerodynamic characteristics in Appendix II
The criteria for the selection of the airfoil design parameters are discussed, as well as the simplified numerical airfoil analysis method used to verify the aerodynamic properties of the new airfoils, are presented.