Validation Naca 0012

mariochelito · March 26, 2017, 12:07

Hi ,

I cant get the same results for drag and lift ? Why are the reasons?

Use turbulence method k-epsilon (2eqn) realizable

Thanks for help

CFD-fellow · March 26, 2017, 23:11

Hi
It depends on so many parameters such as mesh quality, mesh density and right set up.
As u gave just one datum, I give u one clue. K-omega SST should be your first option as turbulence model while you should keep y+ around 1 on airfoil surface.

**Be careful of non-dimensional parameters. If you compare Cl and Cd with experiment results, just take some information of how fluent calculate these parameters. Maybe your results are ok but because of wrong reference values your non dimensional parameters are not calculated properly.
Best regards.

March 26, 2017, 12:07	Validation Naca 0012	#1
mariochelito New Member Mario Chelito Join Date: Mar 2017 Posts: 4 Rep Power: 9	Hi , I cant get the same results for drag and lift ? Why are the reasons? Use turbulence method k-epsilon (2eqn) realizable Thanks for help

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March 26, 2017, 23:11		#2
CFD-fellow Senior Member Behrooz Jamshidi Join Date: Apr 2013 Posts: 110 Rep Power: 13	Hi It depends on so many parameters such as mesh quality, mesh density and right set up. As u gave just one datum, I give u one clue. K-omega SST should be your first option as turbulence model while you should keep y+ around 1 on airfoil surface. **Be careful of non-dimensional parameters. If you compare Cl and Cd with experiment results, just take some information of how fluent calculate these parameters. Maybe your results are ok but because of wrong reference values your non dimensional parameters are not calculated properly. Best regards.