An aero-engine fan and compressor rotor design involves dovetail interface between the blade and the disc, which is critical, as early crack initiation occurs at the interface due to fretting. This paper reviews the different methodologies adopted to understand the fretting behaviour at the interface: experimental, analytical and numerical methods. The effects of geometry and material on fretting behaviour are discussed. The results of a 3-Dimensional finite element analysis of a typical dovetail interface with skew, cone and twist angle are presented. Areas that require attention are highlighted at the concluding section of this paper.