Buckling Analysis of Laminated Composite Panel with Elliptical Cutout Subject to Axial Compression

Table 3

The formulas for predicting the buckling load reduction factors of laminated cylindrical panel.

Equation no.	Range	Parameters	Equations
(3)	0.75≤𝐿/𝐷≤1.75	𝐿𝐷,𝑎𝐷	𝐾cutout𝐿=0.521+0.132𝐷𝑎−1.004𝐷𝐿−0.043𝐷^2𝐿−0.080𝐷𝑎𝐷𝑎−0.017𝐷^2
(4)	0.30≤𝐿/𝐷≤0.50	𝐿𝐷,𝑎𝐷	𝐾cutout𝐿=0.311+1.662𝐷𝑎−0.164𝐷𝐿−1.327𝐷^2𝐿−1.20𝐷𝑎𝐷𝑎−13.015𝐷^2
(5)	0.75≤𝐿/𝐷≤1.75	𝐿𝐷,𝑏𝐷	𝐾cutout𝐿=0.646+0.250𝐷𝑏−2.069𝐷𝐿−0.066𝐷^2𝐿−0.421𝐷𝑏𝐷𝑏+3.166𝐷^2
(6)	0.30≤𝐿/𝐷≤0.50	𝐿𝐷,𝑏𝐷	𝐾cutout𝐿=0.376+1.637𝐷𝑏−0.777𝐷𝐿−1.140𝐷^2𝐿−3.033𝐷𝑏𝐷𝑏+0.529𝐷^2
(7)	0.75≤𝐿/𝐷≤1.75	𝐿𝐷,𝐿0𝐿	𝐾cutout𝐿=0.712+0.204𝐷𝐿−0.999^0𝐿𝐿−0.087𝐷^2𝐿+0.062𝐷𝐿0𝐿𝐿+0.816^0𝐿^2
(8)	0.30≤𝐿/𝐷≤0.50	𝐿𝐷,𝐿0𝐿	𝐾cutout𝐿=0.350+1.684𝐷𝐿−0.399^0𝐿𝐿−1.595𝐷^2𝐿+0.553𝐷𝐿0𝐿𝐿+0.232^0𝐿^2
(9)	0.75≤𝐿/𝐷≤1.75	𝐿𝐷,𝑎𝑏	𝐾cutout𝐿=0.352+0.177𝐷𝑎+0.072𝑏𝐿−0.060𝐷^2𝐿−0.005𝐷𝑎𝑏𝑎−0.015𝑏^2
(10)	0.30≤𝐿/𝐷≤0.50	𝐿𝐷,𝑎𝑏	𝐾cutout𝐿=0.292+1.524𝐷𝑎+0.014𝑏𝐿−1.202𝐷^2𝐿−0.001𝐷𝑎𝑏𝑎−0.008𝑏^2