Abstract: Compressive experiment on the aero short-beam composite stiffened panel was carried out in this paper. The fracture of stiffeners and splitting of panels as well as the failure of either ends are involved in the failure modes. However, the debonding of stiffeners to panels does not appear. At the beginning of loading history, the load-strain curve exhibits linear increasing trend while the out-of-plane displacements are around 0 mm. When the compressive loads exceed the critical buckling load, the strain-load curve tends to branch off. At the same time, there is a drastic rise in the displacement-load curve. The results indicate that short-beam composite also exhibits the post-buckling carrying capacity, which is relatively small. The failure occurs very soon in the short-beam composite stiffened panels if the buckling phenomenon occurs. The results obtained by FE software is consistent with the experimental results. The finite element results indicate that the buckling modes of specimens is the local buckling of panel between stiffeners.