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Heat flux estimation for a liquid rocket engine - UDF

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Old   May 27, 2024, 05:59
Default Heat flux estimation for a liquid rocket engine - UDF
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Vijay Adhi
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Hello! This is my first thread in CFD Online. I'm working on the design of a pressure-fed LO2 and LNG rocket engine. I've been using Fluent to estimate the heat flux for an ablative-cooled engine. I was able to solve all the compilation errors for my UDF.

I'm attaching my boundary conditions and mesh. My model is axisymmetric and I have a fluid-solid domain in my problem, so all my methods are second order. But I keep getting this error whenever I run my calculations.

"Divergence detected in AMG solver. temporarily reducing Courant number to 0.5 and trying again..."

Is there a problem with my mesh? I've used a multi-zone and face mesh with 15 inflation layers.

I've tried all the methods I know to simplify the problem. I still keep getting*the*same*error.
Attached Images
File Type: png BC_Fluent.png (28.0 KB, 5 views)
File Type: jpg Mesh.jpg (115.8 KB, 4 views)
File Type: jpg Inflation layer.jpg (46.2 KB, 4 views)
Attached Files
File Type: txt UDF_hotgas (1).txt (3.4 KB, 1 views)
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