[Nineties123]

Hi,

I'm having a problem trying to do a supersonic run for a NACA 2415 aerofoil on Ansys. I need to get results at Mach 1.2, 3 degrees AoA but every time the solver fails, giving me this error code: ERROR #004100018 has occurred in subroutine FINMES. | | Message: | | Fatal overflow in linear solver.

So far, I have tried:
- Running at Mach 1.3 instead (to see if the tangency of the shock was the problem. Ansys failed again)
- Increasing the top and bottom domain (again, to see if the tangency of the shock was the problem. Failed again)
- Increasing the Memory Allocation factor by 10% (failed again)
- Angling the flow instead of the aerofoil (using Cartesian velocity components at the inlet. Ansys failed)
- Angling the aerofoil (inlet, outlet and openings at top and bottom. Ansys failed again)

Any help would be much appreciated! I am quite new to Ansys.

[aero_head]

Hello,

Did you run your simulation in single or double precision?

If single, switch to double and try running it again (it's a setting you select in solver manager, just select the check box to the right). It's right above the 'large problem' toggle.

Edited to add: I'm assuming this would be a transient simulation, so double precision would make a difference.