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Need Help Calculating Heat Flux in Rocket Nozzle CFD Simulation.

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Old   October 31, 2023, 02:27
Default Need Help Calculating Heat Flux in Rocket Nozzle CFD Simulation.
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Sean
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I am seeking some guidance on the calculation of heat flux within the nozzle. For now I am just using Non-ideal compressible flow in a supersonic nozzle
cfg file and the mesh.
I would like to know the recommended method for calculating heat flux in SU2. Are there specific built-in features or settings I should be using to obtain accurate heat flux results along the wall of the nozzle ?
How should I properly set up the boundary conditions to accurately capture the heat flux at the nozzle's surface? Are there specific considerations for the nozzle geometry?
Once the simulation is complete, how can I extract and interpret the heat flux data from the results generated by SU2? Are there specific post-processing tools or techniques I should use?
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Old   October 31, 2023, 03:37
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Hi,
You can write the heat flux to file using:

VOLUME_OUTPUT= HEAT_FLUX
OUTPUT_FILES=PARAVIEW_MULTIBLOCK


I prefer to use paraview as postprocessing tool. When you write multiblock files, the markers/boundaries are available as individual blocks. So you can then extract for instance only the wall of interest using 'extract block' and compute for instance the total heat flux for this surface inside paraview.


Since heat flux depends on the local temperature gradients at the surface, you have to make sure that the mesh on the surface is fine enough to accurately capture the gradients. Usually inflation layers with y+ < 1 will be a good rule of thumb for accurate gradients.
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Old   October 31, 2023, 03:41
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Could you please let me know how to calculate heat flux here ?
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Old   October 31, 2023, 03:45
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The heat flux is computed automatically inside SU2, you just have to write it to a file. If you want to do it yourself in paraview, you need to construct the temperature gradients normal to the surface.
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Old   November 1, 2023, 06:18
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Quote:
Originally Posted by bigfootedrockmidget View Post
The heat flux is computed automatically inside SU2, you just have to write it to a file. If you want to do it yourself in paraview, you need to construct the temperature gradients normal to the surface.
Could you please help, how I could get heat flux near wall (along the surface of nozzle) in a readable ASCII format?
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Old   November 2, 2023, 07:48
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There is also PARAVIEW_ASCII as output format, and SURFACE_PARAVIEW_ASCII
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Old   November 9, 2023, 07:14
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Quote:
Originally Posted by bigfootedrockmidget View Post
There is also PARAVIEW_ASCII as output format, and SURFACE_PARAVIEW_ASCII
Could you please help me what changes should i make in cfg file so that I see variation of heat flux along the length of the nozzle. Following are my BC's ;

% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
MARKER_HEATFLUX= ( WALL, 0.0 )
MARKER_SYM= ( SYMMETRY )
MARKER_RIEMANN= ( INFLOW, TOTAL_CONDITIONS_PT, 101325.0, 300.0, 1.0, 0.0, 0.0, OUTFLOW, STATIC_PRESSURE, 50000.0, 0.0, 0.0, 0.0, 0.0 )
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nozzle analysis, nozzle cavitation, nozzle simulation, su2

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