How to get an accurate CFD solution to aeroheating problem for hypersonic flows?
Hi, everyone:
I am glad to disscuss CFD with you. I am puzzled with a proplem, which is how to get an accurate CFD solution to aeroheating on body with hypersonic velocity. In my work,I found that heating flux on wall obtained by CFD had large errors comparing with experimental data. Do you have any ideas about that? Thanks! |
If your mach number is > 5 your equations change due to dissociation of molecules. Assuming its less than 5 what numerical scheme do you employ ?
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If the grid is unstructured, a current standard FV code has a big trouble in heating prediction even for a very simple geometry like a 2D cylinder, which I learned from this paper:
Computational Aerothermodynamics Simulation Isues on Unstructured Grids, Peter A. Gnoffo and Jeffery A. White, AIAA-2004-2371, June 2004. |
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Thank you! |
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Thank you! |
I worked in a group where people did similar simulations for a blunt nose with structured grid and obtained pretty good results. I do not remember the numerical scheme they exactly employed but its either ENO or Godunov scheme with a TVD R-K method. I have seen some simulations in AIAA journal which shows the successful application of ENO schemes for flows with shock. MUSCL might be highly dissipative but if you have experimental results, you can always check the contours to see the ability of the scheme.
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