[mauro_minervino]

Dear all,

I was running steady RANS simulations of the transonic flow around a very simple grid and geometry: an isolated elliptic-planform wing (half model, zero sideslip angle). Wing sections are NACA0012 airfoils with closed t.e., and the mesh is made of hexahedra.
No problems at angles of attack different from zero. Nevertheless, I was unable to obtain a solution at zero incidence.
The case at zero angle of attack runs with no difficulty in inviscid conditions (Euler simulation), in viscous and laminar flow, and even with turbulence but in free transition. But when I go for fully turbulent RANS, the simulation blows up.
For the same grid and flow conditions, no difficulty was ever encountered using other flow solvers, either structured or unstructured.
Here below I provide a link to the mesh and configuration files:

https://cirascpa-my.sharepoint.com/:...JaNOQ?e=dBbhB6

Two different formats of the grids are included: CGNS and native SU2. However the problem was encountered with both files.
I used the last SU2 code version (8.0.0), on a Linux HPC cluster with MPI.

Could anyone provide suggestions to solve this issue?
Thanks for your support.
Kind Regards,
Mauro Minervino