Due to the existence of sweepback angle of aircraft, the stringers of the stiffened panels in some parts may be declined instead parallel to the boundary. The paper deals with stability experiment investigation on the stiffened composite panels with tilting stringers. Two panels stiffened by six tilting stringers were manufactured and tested. Attempts were made to obtain the buckling load, ultimate load carrying capability and failure state of the panels. Finite element analysis was performed to investigate the tests and FE models were calculated by ABAQUS. The numerical results were assessed by comparing with the test data and good agreement was observed for both buckling and ultimate collapse load as well as the failure modes of the structure. Further investigation was performed to explore the influence of tilting angles on stability behavior of the panels which revealed that the buckling load exhibited a continuous decrease with the increasing tilting angles while the ultimate load showed an initial rise from 0º to 1º and then decreased.
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