[metmet]

Hi there
I'm going to calculate the drag, lift and moment coefficient of an airfoil in 2D case. I've got good mesh and pressure and lift coefficients obtained from primary runs have good agreement with my experiments. But there is a big difference in drag coefficient. I found that with changing the values in reference values the calculated force coefficients will be changed. but I'm not sure for an airfoil with these dimensions which values are appropriate.
Chord=0.7 (m)
Max thickness=0.14687 (m)
Span=0.5 (m) (the airfoil used in experiments)
Any help is most welcome.