[mihylee]

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%.

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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.

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Please can someone advise me what to do?