Abstract
Numerical predictions of linear buckling and post-buckling behavior of CFRP T-Stiffeners are conducted by Finite Element Analysis. Such behavior is crucially important in aircraft structural design. Comparison between numerical predictions and experimental behavior is executed detailedly. Width to thickness ratio in flange or web mainly governs linear buckling stresses. Inserted filler along the intersection line between flange and web also affect considerably the linear buckling behavior. By taking realistic initial imperfection into account, geometrical nonlinear analysis provides fairly descriptive post-buckling deflection behavior in flange and web. It is also possible to predict the final failure stress by assuming simple failure criteria and non-progressive failure.
