I am a newcomer in this forum. I don't know this question has been asked before or not.

Where do I get the most accurate or fundamental windtunnel result for an airfoil (such as NACA 23012) so that I can compare to my CFD solutions (using PHOENICS).

For example, at Reynold number of 5 x 10+6, there will be different lift curve for NACA 23012 in different books. So there must be some kind of references. Please tell me.

You can check in one of the famous books"Wing sections">>

I suggest you using NACA0012 section to validate your code..much more popular and data is available in most of journals and aerodynamics books.. hope you good luck..