Includes all files necessary for the aerodynamic shape optimization of an airfoil at a constant CL and Reynolds number using a MATLAB-Xfoil interface and a custom conjugate gradient optimizer, using the PARSEC method for airfoil geometry parameterization. The optimization is run from conjugate.m, with the necessary inputs for the optimization of a NACA 0012 airfoil commented out. Reynolds number and lift coefficient are specified in cdmin.m at line 55, but may be modified using global variable definitions. The Xfoil plot display is currently disabled, but may be enabled by commenting out lines 117 and 118 in xfoil.m.
Requires a windows executable of Xfoil, which may be downloaded at: http://web.mit.edu/drela/Public/web/xfoil/.
Note that the standard xfoil.exe output is single precision and thus limits the airfoil optimization. For better results, an Xfoil executable should be compiled for double precision.
Information on the PARSEC airfoil geometry parameterization method may be obtained at: http://www.as.dlr.de/hs/h-pdf/H141.pdf
*** Requires a Windows OS