|August 12, 2013, 05:45||
Join Date: Aug 2013
Posts: 9Rep Power: 3
Hey. I am simulating 2d airfoil (very low reynolds number, laminar, incompressible, transient flow). I am comparing my results (CL) to some published work. I want to know about grid sensitivity rule.
I mean for every angle of attack first I have to use unrefined mesh and get converged result and then check different refine meshes to make it grid independent or just at initial few angle of attacks i should find the best refine mesh and will use it throughout?
Also, I have to refine the mesh in my meshing software (ICEM CFD in my case) or just refining in Fluent is enough (with "Adapt" option)?
My english is not very well, sorry for that.. Please clear my idea about this.. I will appreciate if someone correct me if i am wrong or add more about this.
thanks in advance
|August 17, 2013, 07:20||
Join Date: May 2013
Posts: 20Rep Power: 4
i had a similar problem as yours,
at first, i refined my mesh with ansys for first and second angel of attack, and check mesh dependency and found that with two step mesh adapt on the boundary the results had no differences, then did others case with two step adapt. of course, for last case, i check it again and didn't see any change.
also, you can adapt in the mesh softwarte or in the ansys
|Thread||Thread Starter||Forum||Replies||Last Post|
|[ICEM] Export mesh statistics for use in Richardson Extrapolation for grid sensitivity study||RicochetJ||ANSYS Meshing & Geometry||12||January 18, 2014 19:57|
|[TGrid] grid sensitivity||adil6208||ANSYS Meshing & Geometry||0||January 21, 2010 02:06|
|Grid sensitivity analysis||darookie||CFX||2||August 25, 2009 09:00|
|grid sensitivity test||Joe||Main CFD Forum||1||January 10, 2007 09:08|
|Combustion Convergence problems||Art Stretton||Phoenics||5||April 2, 2002 05:59|