Bear in mind that the lift and drag coefficients of airfoils vary considerably with Reynolds number. I have a lot of old wind tunnel-derived information on various airfoils that does not state the Reynolds number that the airfoils were tested at, and thus the information is useful as a rough guide only.

For example, the NACA 0015 airfoil, very commonly used for aerobatic models, shows peak lift coefficient ranging all the way from 0.83 at Reynolds number 43,000, up to 1.55 (87 percent higher) at Reynolds number 3,300,000.