The nonlinear effects of geometry, material and contact are considered, the finite element analysis（hereinafter FEA） method of composite stringer out-of-plane tension failure is established precisely by using Hoffman material failure criteria and Newton-Raphson increment iteration method. A verification test is designed to test the failure load and failure mode of three different stringer configurations.Then the load-displacement curve is drawn to verify the validity of the FEA method.The influence factors of out-of-plane tension failure of composite stringer are studied, which can guide the strength design of aircraft.