[hxax]

I can't land the simulation on experimental values (Theory of Wing sections) for a NACA foil the drag specifically, both for 2D and 3D. Been through it all.... I really mean it! If i get the drag right, the lift is off, and vice versa. I am talking about values around +20% drag with the lift correct.

- mesh; all kinds
- solution -> cell base size, all reasonable sorts
- boundary layer layout; Y+ wall distance estimation -> first layer wall distance, number of layers, stretch factor etc.

I've been testing so much back and forth that there cant be much else to alter than the actual physics models. Is there a guide somewhere?

[SimulatorMaster]

Hey

Perhaps it could be due to the quality of the mesh you are generating. It would be nice to see the mesh you have created.

If you are using fine mesh around the wing, then this is a low y+ approach in which you are pretty much solving the boundary layer without needing the wall functions. However, if you are using a coarse mesh, you may need wall function to model boundary layer behavior.

Consider using considerable amount of prism layers starting with very low wall thickness (you can change the option in prism layer) and slowly stretching to core mesh. IN these types of sims I generally prefer using trimmer mesh since you can actually form a very smooth transition from prism layer to the core trimmer mesh (Maximum Core/Prism Trans. Ratio)

Also, create volumetric mesh at the leading and trailing edge of the wing.

Not to promote or anything but I have created a video guide in which that you can follow the meshing part. (It involves an overset meshing which you can ignore but make sure to follow the volumetric meshing part where I create parts to do that)
Here is the link: https://www.youtube.com/watch?v=Fs8DoE1iUFU

Hopefully it helps.

Take care