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NACA 0012 drag coefficient accuracy

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Old   August 21, 2018, 18:30
Default NACA 0012 drag coefficient accuracy
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MH Lee
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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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Old   August 21, 2018, 19:11
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Glenn Horrocks
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You appear to be using Fluent. Try the fluent forum.

Also read this FAQ:
Note: I do not answer CFD questions by PM. CFD questions should be posted on the forum.
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