[sonic109]

Can anyone tell me what could be the possible reason that I am getting static pressure contour as in the attached pic?
I have meshed the domain in ICEM and imported it into fluent.
Here are the parameters that I have used-
Re-1.4e05
alpha= 6 degrees
airfoil= GOE 233
Model is SST K-omega
Turbulent intensity= 5
Viscosity ratio=10
y+ = 1

[flotus1]

In your opinion, what is wrong with the pressure contour?

[sonic109]

Well, away from the airfoil, that is at far field, pressure should be same everywhere, not affected by the obstacle. But it is varying since that contour line is spreading to the far field.
Also there is a huge error in values of Cl and Cd I am getting. The mesh is fine, only there is a huge aspect ratio. But that is expected in such type of analysis, right?
Should I increase the wall distance? I thought this much would be enough.

[flotus1]

You dont have to rely on guesses when determining the correct distance of the boundary conditions. Just do a sensitivity analysis to check the influence of the distance on the variables of interest (coefficients of lift and drag in your case).

Since the values you get for cl and cd are way off, I suppose the reference values are different than those used in the analysis you are referring to. Check if you entered the correct reference values in fluent.
And check if the dimensions of your mesh were imported properly (mesh -> check).

Then a value of 5% for turbulence intensity seems quite high for an external flow. It should not severely affect the results for lift and drag coefficients, but I would rather take a low value like 0.1% or even smaller unless you know that the free stream is highly turbulent. Same thing for the turbulent viscosity ratio.

[sonic109]

Checked everything and found out that the problem was with the reference values, as you have mentioned. I know it's really silly.
Thank you for your reply.