Composite sandwich panels are progressively being employed in the aircraft industry for floor panels, compartment partitions, bulkheads and even the skin and wings of aircraft. Lightweight structures are essential for aircraft operations because they allow for faster take-off and landing. The sandwich panel comes into play in this situation. Composites with stiff, high-strength skin facings are bonded to a low-density core to form multi-layered materials with a high mechanical strength. Using finite element analysis and experimental equipment, composite sandwich panels are constructed, tested and evaluated under various load circumstances. The panel's expected compressive strength and flexural stiffness values were then calculated for various operating conditions. A mean difference of 0.28 is seen between the stresses in both x and y directions of the panel over a loading range of 1kg to 60kg. The standardised values of the strains were used to compare them using Bayesian estimation, which outperforms the t test. Ec increases by nearly 20 times when the side length is increased by 10% compared to when the side length is increased by 50%. For a given span length and when an is fixed, the flexural stiffness at f1=0.002 is nearly 2 times higher than that at f1=0.006. Although there are differences in the displacements and strains, the overall trend is fairly pleasing. The exact numerical conditions were not produced due to the experimental challenges, but the loading and displacements were equal.