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Comparison of fluent and CFX for turbomachinery

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Old   May 27, 2011, 08:52
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Quote:
Originally Posted by ghorrocks View Post
Well, the segregated solver does not introduce errors - it just has a looser coupling between the momentum and pressure/mass equation and therefore if the coupling is tricky it makes convergence more difficult. A properly converged segregated solver will be as accurate as a equivalently converged coupled solver.

Segregated solvers iterate much faster, so for cases where the tight coupling is not so important they are superior. For instance you will find segregated solvers often out-perform coupled solvers in transient simulations.
yes you are right
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Old   August 29, 2011, 09:28
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Hello Far,

How you simulated in CFX using the S-A turbulence model? As I know S-A is not implemented in the CFX Solver
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Old   September 5, 2011, 07:26
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ya I did. It is implemented as the Beta Feature, and can be activated in CFX Pre
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Old   September 7, 2011, 15:08
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any success in using SA model ?
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Old   September 7, 2011, 15:50
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No. Do you refer in CFX pre Beta version is implemented?

I read all the CFX manuals and did not find anything about S-A model. Just one model of one equation developed by Menter.

Thank's
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Old   September 8, 2011, 06:24
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Check out this pdf file and you find that SA model is implemented in CFX (from CFX 11 and still as beta in V 13)
http://www1.ansys.com/customer/userg...2.0-update.pdf
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Old   September 8, 2011, 06:43
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http://www.ansys.com/staticassets/AN...tech-specs.pdf


it surely contains the reference that CFX has SA model as beta feature. It should be noted that there are no details given in CFX help regarding beta features.
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Old   September 14, 2011, 15:24
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Nice. I will try to find the beta feature.

Thank's a lot.
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Old   September 14, 2011, 16:28
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it is very much simple. Attached files describe how to activate the beta features
Attached Images
File Type: jpg beat_features_CFX1.JPG (17.6 KB, 48 views)
File Type: jpg beat_features_CFX2.JPG (35.5 KB, 84 views)
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Old   April 3, 2012, 21:08
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Hi Far

I am trying to model NASA Rotor 67 with fluent . but I have alot of problem. I can obtain the correct pressuare ratio for near pick efficny but in other cases i am not able.
Could please give me more information about you fluent case setup of NASA Rotor 37 ? in fact i dont have the grid coordinates and the experimental datas for Nasa Rotor 37to start modelling that.

I will be too much thankful to recive your help and suggestions

Best
Mehdi
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Old   December 22, 2014, 06:21
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which type of boundary conditions did you use in FLUENT? did you use turbo specific non-reflecting BC ?
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Old   December 25, 2014, 14:54
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These were standard boundary conditions
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Old   December 26, 2014, 19:11
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This is actually a fantastic and informative thread.
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