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May 9, 2001, 22:06
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about combustion in fluent
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Guest
Posts: n/a
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Hi,
When I use couple solver,finate rate model,massinlet boundary(subsonic)and pressure-outboundary(supersonic)to simulate all the flow in rocket moter(including nozzle), I get the result of cold flow,then I patch temperature to spark.I find the temperature is very high.After handrands of interation,there is error message: divergence detected-temporarily reducing courant number 0.5 and try again... divergence detected-temporarily reducing courant number 0.05 and try again... divergence detected-temporarily reducing courant number 0.005 and try again... divergence detected-temporarily reducing courant number 0.0005 and try again... divergence detected-temporarily reducing courant number 5e-5 and try again... error:internal error at line 688 in file"rp-mstage.c" divergence detected in AMG solver error object  )When I use segregated solver,finate rate model,massinlet boundary(subsonic)and outflow(subsonic)to simulate some part f the flow in rocket moter(not including nozzle,just the flow of chamber in rocket motor ),I get the result of cold flow,then I patch temperature to spark.And I also set under relaxtion  ressure:0.8,monument:0.25,and other scalars:0.5.After handrands of interation,there is message about reversed flow.After handrands of interation,there is error message: divergence detected-temporarily reducing courant number 0.5 and try again...divergence detected-temporarily reducing courant number 0.05 and try again... divergence detected-temporarily reducing courant number 0.005 and try again... divergence detected-temporarily reducing courant number 0.0005 and try again... divergence detected-temporarily reducing courant number 5e-5 and try again... error:internal error at line 719 in file"amgif.c" divergence detected in AMG solver error object )If I just simulate the flow in chamber,I don't how to define the boundary at the end of chamber.I used the outflow boundary,but reversed flow come into being.If I define pessure-out boundary,I don't know how to define the value of pressure and temperature. Would you give me some advice?Any ansnwer will be welcome. Thank you. Mark 2001.5.10 |
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May 10, 2001, 14:36
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Re: about combustion in fluent
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Guest
Posts: n/a
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Try using the double precision version with a smaller courant number (e.g. <= 1.0 ) and see how it goes. Also make sure that your boundary conditions are correct, especially temerature. Initialize the data field with some reasonable values should also help.
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December 31, 2016, 07:17
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reducing corant number.
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New Member
dd
Join Date: Dec 2016
Posts: 1
Rep Power: 0  |
I faced same problem in ansys 14.0 during analysis of rocket nozzle.The notification comes like temporary reducing corant number.do what should I do?
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