Stanford's website has a wing analysis program on it's website (http://aero.stanford.edu/WingCalc.html) which plots the Cl across the half span of a single tapered wing at a given angle of attack. The input parameters are aspect ratio, quarter-chord sweep, taper ratio, and twist.

Hopefully someone here has knowledge of the discrete vortex Weissinger computation used. My question is what are the assumptions in this calculation process? Does it assume an identical airfoil at every station, scaled appropriately? Or would the plot be valid regardless of spanwise airfoil change? It would seem to me that the Cl at a given station would depend on the airfoil section used at that station.

Thanks