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January 28, 2021, 03:23 |
Ansys CFX Problems running Supersonic
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#1 |
New Member
Join Date: Dec 2020
Posts: 14
Rep Power: 5 |
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. |
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January 28, 2021, 09:51 |
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#2 |
Senior Member
Kira
Join Date: Nov 2020
Location: Canada
Posts: 435
Rep Power: 8 |
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. Last edited by aero_head; January 28, 2021 at 22:45. |
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