Hi! Can someone help me, please .. I intend to do a 2D flow analysis of a wing with flaps assembly, but in defining the dimensions of the computational domain I've encountered a problem: the computational domain coordinate system does not correspond to the wing sketch coordinate system. So my question is how can I set the two coordinate systems so they fit?

Regarding the 2D computational domain, since your model if perfectly symmetric the 2D computational domain will perfectly locates at the center of the part where sketch is shown. On the other note, if your concern is why the C-domain for 3D or 2D is larger that the airfoil geometry, this is due to external flow analysis option which you chose in the setting. As a reminder, the external flow boundary condition must be sufficiently far from the object wherein variations if flow gradient parameters become negligible. I hope I am not missing anything here, but please let me know, should you have any question.