[k_zamzam]

I am using k-w SST model to simulate flow over an airfoil in 2D, I am a beginner to ansys Fluent so I use the default settings , I am simulating it at a Reynolds number of 1 million. The coefficient of lift has a slight error while the coefficient of drag is usually much higher than the correct result. I read this somewhere on this website and I think maybe its the problem ( "Modeling the NACA 0012 airfoil without a trip wire is more complicated, since Fluent itself is unable to predict the point along the chord where the transition from a laminar to a turbulent boundary layer takes place. One option is to manually set this transition point at Re = 5e5, which is the flat plate transition point" ) so does anyone has any idea ? please help!Also can anyone tell me the correct setting for using the k-w SST model , i also tried using unstructured and structured mesh and there is no difference in results