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Abstract
This paper aims to develop a closed-form semi-empirical formula for predicting the buckling load of simply supported and clamped supported composite panels with a circular cutout subjected to uniaxial and biaxial load conditions. The finite element method (FEM) was used to develop and validate the semi-empirical equation. The effective moduli approach for lumping layers was used to transform the laminated panels to anisotropic panels. The proposed semi-empirical formula was developed as a function with respect to panel dimensions and material properties. The results of the presented formula were found to compare reasonably well with finite element (FE) analysis results and available results from the literature.