A way for determining the interlaminar stresses in composite laminates with arbitrary curved edges is described using the boundary layer equations. A simple and efficient method for the calculation of interlaminar stresses is presented. The method gives a stress field that satisfies the zeroth order equilibrium equations and the stress boundary condi tions as well as the stress continuity between plies. Several laminates with a circular hole are dealt with by the present method. The results indicate that the method is of great versatility and has the ability to perform the analysis of thick laminates efficiently.
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