A comparative study of damage mechanisms governing the mechanical behavior of a [-45/90/45/0]_s HTS40/RTM6 NCF laminate under quasi-static and tension-tension cyclic loading was performed. Intralaminar cracking in 90˚-layers is described assuming the Weibull distribution of transverse cracking initiation strength. Based on the assumption that the non-uniform fiber distribution is the reason for strength variation, the fatigue model parameters are determined using the crack density in a quasi-static tensile test and in a cyclic test with just one stress level. A triggering mechanism was observed when the cracking which starts in the 90˚-layer leads to immediate cracking in the neighboring off-axis layers even if the average stress there is low. In the quasi-static test, delaminations are small even at high strain levels. At low fatigue strain level, a similar behavior was observed, however in high strain cyclic tests, the delaminations are growing faster at the edges and inside the composite. The delamination length is the largest at the edge and it decreases towards the middle of the laminate. The rate of the decrease depends on the interface and the fatigue strain applied. Delaminations which have propagated inside the specimen increase the opening and the sliding displacements of the intralaminar cracks thus causing much larger stiffness reduction than cracks without delaminations.