Learning Forum

[Les Bar]

Hi, I am trying to simulate the external flow analysis of an airplane with Mach 0.75 In general settings ı tried steady, transient, pressure-based, density based. Boundary conditions are far-field and symmetry and the domain is a sphere. But even ı tried with the smaller mesh numbers (4 million- 2 million these are the mesh elements that I tried ) I couldn't get the solutions, it took so long. I tried with SST- k omega and Spalarat Allmaras, Implicit solver green gaus node based, and other things are defaulted. What is your suggestion for this type of problem to get a better solution? Please help me because I think I am gonna lose my mind if I take another error from ANSYS. 

Thank you.

[Essence]

Hello.

What do you mean by "I couldn't get the solutions"? Does the solution diverge or the results are not accurate or do you face any error? Did you try initializing with FMG? Share the mesh, case setup screenshots please.

[Les Bar]

The iterations did not even start.I chose steady,pressure based ( after that ,ı tried density based) and operating conditions for pressure set to zero. AOA is 0,02 

[Essence]

It shows that the generated mesh is poor quality. Please improve the mesh quality (OQ>=0.12 and AR<=400).

[Les Bar]

Yes, but even when I  tried with good mesh it did not work. Is my setup right? I want to know it.

[Essence]

Try using density based solver with FMG initialization. Please refer to the Ansys tutorials for more information.

https://ansyshelp.ansys.com/account/secured?returnurl=/Views/Secured/corp/v232/en/flu_tg/flu_tg_oneram6_wing.html

https://ansyshelp.ansys.com/account/secured?returnurl=/Views/Secured/corp/v232/en/flu_tg/flu_tg_transient_compressible.html