This code is listed on MATLAB File Exchange here: Airfoil experimental database
Get airfoil characteristics from an experimental database.
This app queries an aerodynamic database of NACA 4 digits, 5 digits, 6 series, and NASA supercritical airfoils. Data for the NACA sections has been derived from the book Theory of Wing Sections, by Abbott and Von Doenhoff. Data for NASA supercritical (cambered) airfoil is extracted from NASA TM 81912. The app reports airfoil characteristics, lift curve and drag polar with a few inputs. The user has only to select airfoil family and assign relative thickness and Reynolds number. The characteristics of the curves are reported in a table, which can be exported on a spreadsheet file. All data are at low Mach number, incompressible flow regime. Very useful in preliminary aircraft design, when the user needs a reliable source of data but has only few global parameters to play with.
Open main.m to use the program from the main script. This will allow to plot data for many airfoils. This is not interactive and requires a minimum of MATLAB knowledge, although most of the users only should change input data.
Alternatively, you can use the MATLAB app to execute the program interactively with a GUI or the standalone executable (only for Windows), which does not need MATLAB installed, but may require to download about 800 Mb of data for the MATLAB runtime compiler. Check the binaries on the releases page.