Good morning,
I'm a studying a rectangular wing with NACA0012 airfoil in Ansys-Fluent. I get very bad results with contour lines, moreover the CD is not exactly what should me. The simulation involves a wing with 20m wingspan, 5° angle of attack, Transition SST-model and 2000 iterations with first order of discretization and other 2000 with second one. I attach some images of mesh and final results. Is it because I'm doing all the calculus by dividing into two parts the domain and use "symmetry" later?
@Angelini: How about the other boundary conditions regarding the flow field?
It is advisable that you do the benchmark airfoil problem before you proceed with your case. Thereby, you would gain an idea about the physics and hoepfully you can resolve the current issue with ease.
Looking at your results, I would say that the key issue here is mesh design/refinement. No matter what settings you use, your results can only be as good as the computational grid allows it.
What I would recommend is to start off with a 2D section or a narrow 3D slice of the problem, where you can experiment with the correct mesh settings to get accurate results (considering an infinite wing of course). Then once you have a mesh design that works, you can apply that to your larger 3D problem. The advantage is that small, especially 2D models solve in no time, so you can do a lot more iterations/find the correct mesh/settings faster. You can find many airfoil examples online where you can see the style of meshes people most often use.
Sorry but if it is a 2D simulation I can see why that model is symmetrical, I can see the symmetry in any direction. I dont know why your results are wrong but really there is not simmetry in that model.
Thank you all. I have improved the mesh dividing into parts each edges with "Edge sizing", now the results are correct.
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