# Bad Convergence on Complete Aircraft Analisys

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 October 6, 2015, 21:04 Bad Convergence on Complete Aircraft Analisys #1 New Member   Join Date: Oct 2015 Posts: 5 Rep Power: 10 I'm a new user of Star-ccm+ Trying to simulate a canard Type aircraft in the following flow: P = 69820 Pa T = 268.3380 K V = 87.45556 m/s M = 0.2663 Rho= 0.9046 kg/m³ my set up: three-dim steady segregated flow (Green-Gauss) constant density Turbulent K-omega All y+ treatment For some reason I cant get a 1e-4 convergence, not even 1e-3 in the residuals. My mesh is an Unstructured mesh (Tetra) with a prism layer with y+ =32 Here are some pics from the mesh: does anybody has some tip for me so I can improve the convergence?

 October 7, 2015, 19:18 #2 Senior Member   Join Date: Nov 2010 Location: USA Posts: 1,232 Rep Power: 24 Your mesh is way, way too coarse. There's no wake refinement at all. Why are you using an ANSYS mesher and a tet grid?

 October 7, 2015, 21:13 #3 New Member   Join Date: Oct 2015 Posts: 5 Rep Power: 10 i'm using a mesh with 6.6 million cells approximatelly, it is for an article in canard airplanes regarding their aerodynamics in the general aviation. I've never dealt with cfd meshes before as so I was told that the mesh itself was "good". I put 22 layers of prisms for boundary layer calculation wich gives me y+=32. The thing is that I don't know how to make another type of mesh on ICEM other than tet mesh with prisms. I've notice that even though I smooth the mesh till 0.38 minimum quality I keep getting bad quality after building the prisms layers. I'm short on time so I think that any tip regarding geting a good quality mesh (Tet with prisms) will make it work. My computational resourses are somewhat limited to a i7,24gb, 12 cores computer. For now i'm studying the relation between the size of the domain in the calculation of lift and drag which is very difficult because the solver doesn't give me good convergence. Last edited by arthurdiasBR; October 7, 2015 at 21:16. Reason: adding more technical info

 October 7, 2015, 21:41 #4 Senior Member   Join Date: Nov 2010 Location: USA Posts: 1,232 Rep Power: 24 You're posting in a STAR-CCM+ forum, but you seem to be using ANSYS products, which I don't really understand. STAR-CCM+ has excellent easy-to-use meshers. But for a situation like this you should really be using a hex/trim grid or a polymesh. Tets are very diffusive. I guess the good part for you is tets are relatively memory cheap. 6.6M cells is pretty coarse for aero. With your CPU limitations I would cut the number of prisms in half and spend more on wake refinement. Lower the growth rate around the aircraft and do wake refinement. It should be very easy to see where your total pressure gradients are too coarse if you do some cutplanes. You are very limited on memory resources, you can probably max out at 16M or so cells. If by quality you mean skewness, 0.38 is very good quality for Fluent's skewness criterion. You can probably put your worst cell at 0.75 or so and be fine. If that's STAR-CCM+'s cell quality criterion, you can probably lower it to 0.1 and be fine.

 Tags aircraft, convergence, set-up, solver control, star-ccm+

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