Abstract: In modern days, composite materials play a major role in many applications specifically in commercial aircraft due to its high specific structural properties and high corrosion resistance as well as being relatively lightweight compared to their metal counterparts. These features that composite materials possess facilitate the designers to come up with various possible designs with high structural efficiency. Subsequently, numerous alternatives in varying fiber orientations have been studied over the years in order to customize in-plane stiffness which leads to enhanced structural performance, especially buckling performance. This paper presents a finite element model of conventional straight fiber and curvilinear fiber composites with respect to compressive load considering different boundary conditions. The variation of orientation variation and buckling load will be investigated for curvilinear fiber composites. And finally the results will compared with the conventional straight fiber composites.