Hi, I am simulating a 1 meter span naca0012 wing (no taper, just extruded airfoil). I have meshed half domain 0.5m span wing and applied symmetric boundary conditoin. How can I get the torque by actual 1m span wing around any specific point? Reference length is 1 meter. Thanks for your help. Endee

Just to explain my question further: If I calculate the Cm of NACA0012 in 2D and then in 3D (1 m span), with the same reference values in both cases, should the Cm be matching ideally?

hi dear m doing the same problem. If u got the result, that will be my pleasure if u give me some instruction. I have all ready plotted the airfoil in 2d and 3d. But what will be the exact boundary condition??