The Classic Laminate Theory analysis described in the following sections can be evaluated using the Sampling Point, Stack-up and Sublaminate Properties. In a Sampling Point, the laminate properties and stiffness/compliance matrices are evaluated based on the lay-up on the shell mesh. The changes to the lay-up incurred by solid model operations (Extrusion Guides, Snap-To and Cut-Off operations) are not considered. The laminate forces can only be evaluated if the shell mesh has a solution with nodal deformations.