Abstract: In order to determine cross-section size parameters of the horizontal stabilizer plane of a certain aircraft, and validate that the simulation analysis method is reasonable and effective, axial compression stability of composite stiffened panel was studied by finite element buckling analysis and tests. Under the condition of the same support, it was researched that the tendency of the initial buckling and bearing capacity for composite stiffened panel caused by increasing the ratio of stringer cross-section area occupied the whole cross-section area. Test results show that test results and calculation results are consistent, which prove that the analysis method and analysis model are accurate and effective. The buckling loads would increase about 10.0% with the ratio of stringer cross-section area increasing 3.0%. This result would be used to guide the composite stiffened panel design work in aircraft type development, and provide reference for whose preliminary determination of the types and parameters of cross-section for horizontal stabilizer plane.