Too low Cl values
 

hello everyone!

I'm new at Fluent and CFD in general. I'm trying to get lift and drag coefficients of NACA4412. Whatever i try to do or change, mesh, BC, etc, i don't get even a close result for values i found on airfoiltools.com.
for exemple, at AoA of 10 deg i suppose to achieve Cl=1.3 while the closest result i get is Cl=0.4.

Re=1e6
c=0.3
Viscosity model ->K-omega SST

on the Cl monitor i tried to defined a vector (-sin(10),cos(10)).

Thanks, Nir