[TempestCFD]

Hey guys,

I'm trying to model a 3-D wing in Fluent to study the effects of boundary restabilisation via Vortex Generators.

I started by using the k-e model, before realising that this was inappropriate for the high angles of attack I would be studying. I have now tried to switch to k-Omega SST to better capture boundary layer separation, and refined my mesh (50 layers of inflation, first off wall thickness of 1e-06 due to a fairly high Reynolds number of ~ 10^5). My domain is about 20 chord lengths radius (I have a cylinder) of my wing, and I'm using a pressure-far-field condition.

My solution doesnt last too long before it starts to diverge, and I have no clue why. I have been searching all over the forums for a good two days trying to solve this issue, but without any luck.
Any ideas?


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Also, here are some of the parameters that I have set (just to reference):

1) Pressure Based, Steady
2) Energy - On, SST k-omega
3) Air - ideal gas (for pressure-far-field condition)
4) Velocity - 13.44 m/s
5) Courant # of 5


Attached is a picture of part of my mesh.


Thank you for your help