A first ply failure analysis of a composite laminate using Hashin type failure criterion is carried out. The failure results in the .f06 file indicate a "failure mode" which are numbered 1 - 4. As I understand it, it is indicating the dominant failure mode - fiber tension/compression or matrix...
I am trying to extract composite laminate stresses from NASTRAN. I have read in the NASTRAN manual that the Elements stresses options yields incorrect results. How should I go about calculating the laminate stress from the individual ply stresses?
