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I'm trying to apply pressure loads on an aircraft wing. I've created a .csv file for the same . the first column of the file represents the wing chord, second column represents the wing span and the third represents the pressure magnitude(figure attached). When I apply this load on the wing, the pressure is not applied normal to the elements (figure attached). I've checked the element normals and they all point outward. I'm not able to figure out why the pressure is not being applied in the normal direction. Please suggest solutions. Thanks.