Carbon Fiber-reinforced polymer composite materials are fast gaining ground as preferred materials for the aero
engine components. For the easiness of manufacturing instead of traditional fiber and resin layup process, the composites are
manufactured using laminate sheets of composite made with layers of prepreg (carbon fiber pre-impregnated with Resin) sheets
which are stacked with different ply orientation (Ex: +45°,-45°). For different size and shape of components only standard size
prepreg sheets are available. While doing layup process gap between two prepreg sheets is unavoidable. These gaps may cause
some weak spots in the laminate. While fabricating the components these weak spots in laminates may overlap when stacked
which further weakens the component. To study the impact of such weak spot overlap, complex FE analysis is required which
may take significant efforts. However, it is possible to avoid such complex FE analysis if there is methodology in place which can
prove that the occurrence of weak
