Delamination, induced by interlaminar tensile and shear stresses, is the primary failure mode for composites. Through matrix cracking, delamination destroys the structural integrity of an aircraft’s structure. Numerical Modelling was used for interlaminar progressive failure analysis of the cracks. Dr Raju’s paper on Interlaminar Progressive Failure Analysis of Composite Curved Aircraft structural components using MSC MARC was adjudged the best paper at the MSC User Conference. Click here for the presentation.