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Need Help Calculating Heat Flux in Rocket Nozzle CFD Simulation. |
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October 31, 2023, 03:27 |
Need Help Calculating Heat Flux in Rocket Nozzle CFD Simulation.
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#1 |
Member
Sean
Join Date: May 2023
Posts: 52
Rep Power: 3 |
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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October 31, 2023, 04:37 |
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#2 |
Senior Member
bigfoot
Join Date: Dec 2011
Location: Netherlands
Posts: 670
Rep Power: 21 |
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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October 31, 2023, 04:41 |
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#3 |
Member
Sean
Join Date: May 2023
Posts: 52
Rep Power: 3 |
Could you please let me know how to calculate heat flux here ?
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October 31, 2023, 04:45 |
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#4 |
Senior Member
bigfoot
Join Date: Dec 2011
Location: Netherlands
Posts: 670
Rep Power: 21 |
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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November 1, 2023, 07:18 |
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#5 |
Member
Sean
Join Date: May 2023
Posts: 52
Rep Power: 3 |
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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November 2, 2023, 08:48 |
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#6 |
Senior Member
bigfoot
Join Date: Dec 2011
Location: Netherlands
Posts: 670
Rep Power: 21 |
There is also PARAVIEW_ASCII as output format, and SURFACE_PARAVIEW_ASCII
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November 9, 2023, 08:14 |
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#7 | |
Member
Sean
Join Date: May 2023
Posts: 52
Rep Power: 3 |
Quote:
% -------------------- 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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Tags |
nozzle analysis, nozzle cavitation, nozzle simulation, su2 |
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