hello martin,

reference area should be equal to chord length (in meter)* 1meter for 2D simulation of airfoil and in the velocity option you should input your velocity of the flow simulation.

in your current reference values reference area seems ok. i think the error might be due to improper viscosity model selection. which model do you used?

The viscous model I am using is the k-epsilon model.

i think the problem is you are using turbulent models for viscosity where as your flow is in laminar region since your reynolds number is lower that fall in laminar region. you should apply laminar viscosity model and check what happens

With this viscous model set to laminar, the simulation does not converge. I applied the 1eq Spalart-Allmaras model as well to see how it would do but only gave me worse results.

i recently did 2D simulation of airfoil for 400000 Re using SST k-w viscosity model. since your Re 60000 is low i thought laminar model would be best. another thought past my mind if you used inflation layers to thin compared to mesh size. that might cause divergence which happened in my trials as aspect ratio becomes higher.

it's probably because of your mesh, check the y+ and again check the wall distance you've chosen for your BL mesh, use this to calculate your wall distance and Reynolds number.

http://www.pointwise.com/yplus/