DLR F6 solution not converging
 

Greetings all,
I am a masters student of aerospace engineering and i am a learner of fluent. currently i am working on simulations for DLR F6 wingbody junction, a project present in drag prediction workshop. I have done structured meshing of my model and quality of mesh is okay. For the last 15 days i am working on fluent in order to get a converged solution for my model so that i can compare the lift coefficient, drag coefficient and surface pressure distribution with the experimental results present in drag prediction workshop. According to DPW i must get lift coefficient of 0.5 at Mach 0.75, but my solution goes to 0.5 value and then start to diverge to a small value and keeps on diverging. Following are the boundary conditions that i have set:
Inlet: pressure farfield, Mach 0.75, angle of attack 1 degree
Outlet: Pressure farfield, Mach 0.75, angle of attack of 1 degree
Side: Pressure farfield, Mach 0.75, angle of attack of 1 degree
Symmetry: Symmetry
i have used courant number of 0.5, i have used sparalat Allmaras model of turbulance, density based solver.
After some iterations, console window says negative nut value found in 2 cells after linear solve and sometimes 3 or 4. i have completed 12000 iterations but still i am not able to converge my solution to any single value. it just keep getting down and after some time starts to go up but no stable value achieved yet.
If you know the solution of this problem or you have any helpful suggestion for me then reply me to overcome this problem. Thanks
Regards

Solver at M 0.75
 

Though density based solver can be used at any Mach number, it is recommended to use pressure based for M < 2. You can certainly work with density based solver as well, however, this would require a better initial field and may be solution steering.

solver at M 0.75
 

Okay i will try to do simulations using pressure based solver as well. is there any other thing that might be the reason why my solution is not converging. i mean any mistake in the details that i mentiined about my model？i appreciate your suggestions

Case Setup
 

Rest of the setup appears alright. Ensure that the ideal gas law is used for material density and operating pressure is set to 0. Try using fmg initialization. If the fmg initialization is successful, then the simulation should run fine. If not, then there is some issue with the setup.

Thanks
 

Thank you so much for your kind help. i will do as you told me and if i have any problems then i will reply you if you do not mind 😊

initialization
 

i have used standard initialization and compute from inlet. the operating pressure is 0. is it okay？

error in simulations
 

when i tried to use pressure based solver, it gives error that says floating point exception and also a warning that limited wall distance for 2361 cells to 10^-12. what should i do noe brother？

Mesh
 

Did you create an extremely fine mesh? Limiting the wall distance means you have boundaries with very small or highly skewed cells. Run a mesh check in Fluent and then may be try a case with lower Mach number.

Standard Initialization is not good for such cases. Use fmg-initialization. You have to use command to do that

solve init fmg-init

Mesh check
 

okay brother i will check the mesh quality and i will also run fmg initialization. lets see if i get my problem solved

Mesh problem
 

brother i have check the orthogonality of my mesh. when i check it in icem, it shows min of 0.38 but when i convert it into unstructured mesh and import in fluent, it shows a very low min orthogonality of the order of e^-7 and gives warning the orthogonal quality is below 0.01.what is this matter brother？can you tell me why is this happening？

Orthogonal Quality
 

ICEM and Fluent have their own definitions of orthogonal quality. If Fluent observes OQ below 0.01, it would be difficult to get good results. With 1e-7, it's better to improve the mesh. Closer to 0.01, you can still work with Fluent using low URFs and/or Node based gradients. Furthermore, try to improve skewness of the mesh; skewness is more important than OQ.

Mesh problem
 

Thank you so much brother. i will work on improving skewness and orthogonality and then do my simulations. Thanks for your advice 😊