[PierceH]

Hello,


I have a resolved wing on Fluent and want to extract sectional drag at given locations. I tried to do this by creating slices on my wing then performing a surface integral summation of a custom field function that for pressure drag would read X_face_area*Cos(AoA) + Z_face_area*Sin(AoA)*P_static. And to verify this will integrate to pressure drag if I am doing so for the whole aircraft, so there's no issue with this setup. However if I do it for a 2D wing section, I then have the issue where the face areas are not 2D, they're for the entire cells where the desired section cuts the surface grid and so I have a drag value that is acting over a given area and then how do you calculate that area....



Any suggestions?