[xTamx420]

Hi, I am trying to model a sort of extended foil shape 2D section and I would like to get a second opinion on the setup. The shape is a narrow rectangular section with the leading edge of a NACA foil on the front and the trailing edge on the back.

The flow is moving at 0.5 m/s with no angle of attack and the reynolds number is around 415000. I chose laminar flow for the simulation but I got some results that were unexpected. I think it is either because of vortex induced vibration or I chose the wrong viscosity model.

The mesh has more than 300000 elements and is a C-shaped mesh.

Any comments on this setup and model choice would be appreciated.

[AdrienL]

Hi,

the best for an airfoil profil in Fluent is to do the geometry as shown in the picture and use a far field fonction on the outside.
You should also think about adding prism layer (3 would be enough) around the airfoil and use a k epsilon realizable with enhanced wall treatment viscosity model

sincerly

Adrien

[xTamx420]

According to the reynolds number the flow wont be fully turbulent, which is why I close laminar flow. Are you saying it will be turbulent?

Tom

[AdrienL]

Yes, it will be turbulent because the velocity will increase near the naca profil.
So you should use a k epsilon model (or spalart allmaras if the computing is too slow).

[xTamx420]

Right, I forgot about that. I will give your suggestion a try then. One question though, what do you mean by a prism layer?

[AdrienL]

I mean the cells that will enable you to get the boundary layer