[diogoncsa]

I have been modeling some airfoils to test its aerodynamic properties and when comparing to air tools database the values are very different.

I was expecting the lift coefficient somewhere near 0.6 and I am getting 0.10375 and was expecting drag coefficient near 0.1 and I am getting 0.00505


I am using 20 m/s speed at x-direction only at the inlet boundary condition (velocity inlet) and the outlet as pressure outlet with 0 gauge Pressure. The mesh seems ok since I already did validation tests and the maximum y+ value is 4 (using RNG k-epsilon, the maximum y+ should be less than 5).
One thing I noticed is that the dynamic pressure on the upper side of the wing is higher than the lower side. For the absolute pressure, however, on the upper side is shorter than the lower side.

Any idea on where to tackle this problem? Where should I look at?