According to related calculation parameters, this paper compares the buckling critical value calculated by the function for orthotropic composite panel subjected to shear loading with the experimental results of a batch of typical test panels for an airplane program subjected to shear loading. The results show that the original skin lamina thickness considered, the width of the panel related with the stringer foot, four edges simply supported, five theoretical results get fairly well with experimental results, and the absolute error between theoretical result and experimental result is within 5%.