I've been trying to get accurate lift and drag coefficientsof a naca 2412 for days now and have finally started making someprogress. I've took someones advice here on increasing the boundaryto 200*c and the lift coefficient is now pretty close. However, thedrag coefficient is still about double the experimental value. I'vetried changing the turbulence boundary and testing at different aoaand reynolds number. Any ideas what I could be doing wrong? I heardthat drag is difficult to get accurate results with, is that truefor even low aoa and moderate flight conditions?

Also, what is the best way to create a mesh for this simulation? Itseems like I can only refine the mesh is horizontal and verticalbands or very closely around the airfoil. When i refine the mesharound the airfoil using to local mesh tool, it creates many extracells along the z-dir instead of leaving it at 1 cell for 2dsimulation. Thank you and sorry for themany questionsSolidworksFlow Simulation