[zloty001]

Hello,


I am beginner in opensource CFD and it is my first - non tutorial - SU2 simulation and here is short description of my case issue.


I have some trouble with coverage compressible simulation over airfoil (M=0.85). I ran my calculation and residuals are not "going down" so I stopped SU2 after 1000 iterations. To compare in Fluent it took me about 300 iterations to converge solution. Moreover comparing to Fluent solutions, the SU2 solution has a hudge difference (Cd in Fluent: 0.0643, Cd in SU2: 0.13). I don't know why the difference is so huge and how to make my results more accurate.


My config file is based on turbulent NACA 0012 tutorial although I made some changes, but in my opinion it shouldn't be a problem. Nevertheless, I attach my config, maybe I am missing something. I would appreciate if someone could see into it. I used Multigrid as it should make calculation converge faster and I used linear solver as well.

My second though "why can't it converge' was that it is due to mesh. I made structured mesh in ICEM and in my opinion it is fine. I would be grateful if someone could look into it. Moreover, I am thinking whether triangle mesh would be better to calculate for SU2?


Below I attach only residuals plot.
Here you can see config file, mesh and results (SU2 and Fluent to compare). https://app.box.com/s/hqseqg9qds2l0h8ivz5asziuurv7qhq0

Maybe one more sentence, why I am using SU2. This is because I am doing CRM wing optimization project on my University. I am going to optimize 6 section of CRM wing and compare "2D wing optimization" (through airfoils optimization) to the whole 3D wing optimization.


Thanks in advance for your help !