a airfoil problem

Hi, guys:
I got a problem about airfoil which puzzled me presently, for I am designing my midget, and for lack of wortmann laminar airfoil detailed data which I long forward, so I have to fall back on the naca 4412 temporarily, I found two naca reports, in which indicated that 4412 could reach 0.6 at angle of attack of 2 degree under the condition of Re=3 million and aspect ratio of 6, but in the another report which published by Russian show the naca 4412 CL at 2 degree angle of attack can only reach 0.45, which one is correct?? Below is the polar graphics, the first graphic is the Russian’s.