Where can I find full wing polar data to validate an aerodynamic code?
"Theory of Wing Sections" by Ira H Abbott and A. Von Doenhoff has extensive graphed and tabulated data for Cl and Cd vs alpha of a wide variety of wing sections. 

Airfoiltools.com has also got a lot of the data you're looking for, but from a quick scan it doesnt appear to cite their sources. The data is readily available in tabulated format, however.

In either case, its not explicitly mentioned but I'd assume that the data provided is for wings of straight planform. I'd guess that you can find some kind of formula to account for the difference either in the Abbott book mentioned or elsewhere, possibly applying a variation of the blade element method.