The aim of this work was the mechanical characterization of different RTM-laminates. The fibre preforms, so called non-crimp fabrics, were made of carbon fibres. The influence of different fibre-types, resin-systems and lay-ups was analyzed and the significant properties under monotonic tensile and compression load (stiffness and strength) as well as the fatigue behaviour under alternating load were determined. The characterisation of the test specimens concerning their length showed an increase in tesile strength of 10 % for the short specimens. Concerning the influence of the fibre-type the HTS fibre showed a higher tensile strength, whereas the specimens with the HTA fibre gave a higher compression strength and a slightly better result in the fatigue tests. Regarding the lay-up of the fibres the biaxial lay-up showed a higher strength and stiffness, for both tensile and compression loads. Also a better fatigue performance was achieved with the biaxial samples. Comparing the different resin systems, it can be concluded that there were just little differences in the mechanical property profile of the several resin-types investigated. Therefore, at least in this respect, alternative RTM-resin systems to the only one qualified in civil aircraft (RTM6) would be possible.