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July 5, 2017, 19:23 |
COUPLED Solver Stability Issues
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#1 |
New Member
Abhimanyu
Join Date: Jul 2014
Posts: 19
Rep Power: 12 |
Hey guys,
I have been performing 3D URANS simulations for Re 3 million on NACA 4415 AR 12 Wing using COUPLED Solver on structured hexahedral grid. I started off by running steady state simulations first using the same solver and got satisfactory results. But when i try to run Unsteady simulations, the result diverges in the first step even though the grid is the same. My momentum urf is 0.2, pressure 0.3 for both steady and unsteady. I have been able to get the solver to run for momentum urf to be 0.05 but the time-variation of CL (lift coefficient) is not realistic. Can anyone suggest a solution to this issue? Any help is highly appreciated. |
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July 5, 2017, 22:45 |
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#2 |
Senior Member
Lucky
Join Date: Apr 2011
Location: Orlando, FL USA
Posts: 5,751
Rep Power: 66 |
You shouldn't be using that small of a urf for transient simulations. Run small time-steps with large urf's (all 1's). Set the courant number to super large value, i.e. 1e7.
Is this compressible or incompressible? Check your courant numbers (acoustic and convective respectively).. |
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July 6, 2017, 00:43 |
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#3 |
New Member
Abhimanyu
Join Date: Jul 2014
Posts: 19
Rep Power: 12 |
Incompressible.
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July 6, 2017, 16:22 |
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#4 |
Senior Member
Lucky
Join Date: Apr 2011
Location: Orlando, FL USA
Posts: 5,751
Rep Power: 66 |
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Tags |
coupled, fluent, vorticity, wing, wing tips |
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