Fluent
 

Hi, I trying to validate a flow around an airfoil in fluent in respect with experimental data. At low angle of attack it's ok, but at about 8 degrees I start do get cl values very diferent (lower) from the experimental ones. Well,I using SST with transitional correction (it's a flow around an airfoil similar to Selig 1223 at Reynoldy Number 300.000). The inlet condiction is I=0.0034 and viscosity ratio 10.That are good inital guesses? Could you tell me how to solver this problem? It's necessary to correcty some data to diferents values from that used at lower angle of attack?

Sorry by the lack of knoledge,I'm student and I learning to use fluent just for 2 months.