NACA0012 Data as a function of Re for a VAWT model
 

I need reliable NACA0012 lift and drag data as a function of both Re and angle of attack for use in a double multiple streamtube VAWT model in the range 1e4 < Re < 1e6. I have a Sandia report that has experimental data for Reynolds numbers 1e4, 2e4, 4e4, 8e4, 16e4, 36e4, 7e5 and 1e6. Should I just interpolate these numbers or is there a more accurate method? Should I for example use XFOIL to get the data for finer intervals? Which method would yield best results?

Also, what is the preferred airfoil to use with a Darrieus-type VAWT? I chose NACA0012 based only on the fact that that's the only profile I have at least some data. Should a cambered or perhaps some different NACA00XX airfoil be used instead?

The NACA0012 is used frequently in VAWT research because CL, CD and CM are available for the full range of AOA and for a wide range of Rn. In practice, airfoils with less dramatic stall characteristics are preferable. Cambered airfoils can help self-starting a little, but variable pitch is probably a better way to go if lack of starting torque is an issue.