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July 20, 2022, 00:46 |
Divergence of CD Nozzle
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#1 |
New Member
John
Join Date: Jul 2022
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I am trying to simulate the flow through a simple converging-diverging nozzle with known inlet and outlet pressure and temperature.
Inlet Pressure: 700000 psi Temperature: 3400K Outlet Pressure: 101325 psi Temperature: 300K It is 2-D density based and axisymmetric using air as the fluid. Energy is on and I am using the k-omega SST viscous model. I am not sure what I am doing wrong but the simulation consistently diverges. Below I have attached 1) Scaled residuals chart, 2) Best Mach Contour number produced, and 3) Mesh Quality Stats, all for ~225 iterations. I am fairly new to CFD, so feedback would be greatly appreciated. |
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July 20, 2022, 10:46 |
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#2 | |
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Void_CFD-user
Join Date: Feb 2022
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Quote:
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July 20, 2022, 11:38 |
Solution Methods and Console
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#3 |
New Member
John
Join Date: Jul 2022
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Thanks for the help Indra.
I attached a screenshot of my solution methods. For the next iteration I will change them all to "first order upwind". Just for future understanding, how might changing the solution method to first order allow for convergence? In the console the message "time step reduced in X cells due to excessive temperature change" after every few iterations. X being some number usually between 2-15. I did not want to attach a screenshot of my console because it has some sensitive information. I've also got a message saying "temperature limited in X cells. Edit: still divergence while using first order equations. |
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July 20, 2022, 12:41 |
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#4 | |
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Void_CFD-user
Join Date: Feb 2022
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Quote:
Also, I have seen that AUSM scheme in under flux type is more stable than ROE-Fds for mach number>1.5. As for your questions regarding schemes, first order increases the convergence but it is not as accuracte as second order. So we usually run enough iterations in first order to make sure our residuals drop and then swith to second order. There's also a method to use blended first and second order approach which you can access through the TUI but again, don't worry about it for now. Always change oe thing at a time. For now try changing positivity rate and switch to first order for residuals to drop. |
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December 1, 2024, 11:14 |
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#5 |
New Member
Tariq Mahbub
Join Date: Mar 2021
Posts: 1
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Hi Kepler 12,
Have you been able to sovle the convergence issue? I am facing similar issue while modeling a convergent nozzle. I am having stuck residuals in the order of 10e-1. Thanks. |
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Tags |
ansys, fluent, nozzle, rocket, supersonic |
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