[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%.

​

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?

[ghorrocks]

You appear to be using Fluent. Try the fluent forum.

Also read this FAQ: https://www.cfd-online.com/Wiki/Ansy..._inaccurate.3F