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#1 |
New Member
MH Lee
Join Date: May 2018
Posts: 12
Rep Power: 8 ![]() |
I am testing NACA 0012 airfoil and comparing my results with experimental data.
The lift coefficient results were very accurate (below 5%) but my drag coefficient values are not accurate enough (25%). I want to make it below 5%. These are my fluent setting: - Viscous (SST k-omega) - For solution method, i tested with 'Coupled', 'SIMPLE' and 'SIMPLEC' but not much difference (don't know the exact difference of them) - For solution initialization, Hybrid. Please can someone advise me what to do? |
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#2 |
Super Moderator
Glenn Horrocks
Join Date: Mar 2009
Location: Sydney, Australia
Posts: 17,816
Rep Power: 144 ![]() ![]() ![]() ![]() |
You appear to be using Fluent. Try the fluent forum.
Also read this FAQ: https://www.cfd-online.com/Wiki/Ansy..._inaccurate.3F
__________________
Note: I do not answer CFD questions by PM. CFD questions should be posted on the forum. |
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