Failure stresses for (a) plate specimens of glass chopped strand mat (CSM) and plain weave fabric-reinforced polyester resin laminates containing holes of various sizes, and (b) box-section beams of CSNI/polyester resin laminate containing a notch or hole in the tension flange were determined. Experimental values were compared with predicted values calcu-Iated from separately determined critical stress intensity factor, Kc, values. The Kc values were corrected using Irwin's crack tip zone correction factor together with an equivalent yield stress. For both types of specimen measured and predicted failure stresses were in reasonably good agreement.
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