Diary

Airfoil geometry can be characterized by the coordinates of the upper and lower surface. It is often summarized by a few parameters such as: maximum thickness, maximum camber, position of max thickness, position of max camber, and nose radius. One can generate a reasonable airfoil section given these parameters. This was done by Eastman Jacobs in the early 1930’s to create a family of airfoils known as the NACA Sections. Following Abbott and Doenhoff in “Theory of wing section” I have preparated a simple Fortran90 code ( here you can download the source code ); whit this code is possible calculates only NACA 4 digits airfoil shapes.