The aim of this project was to investigate the potential of using a lattice structure to design an aerofoil for light-flying vehicles like UAVs (Unmanned Air Vehicles). The wing was designed with a two-skin type structure with a lattice in between the skins. The material used for this was Nickel-Titanium, commonly known as Nitinol. Nitinol exhibits a phenomenon known as superelasticity. This project aims to combine the strength and superelasticity phenomenon of Nitinol so that it can be exploited to design an aerofoil capable of bending under the application of stress. Using a lattice structure enables this as this phenomenon is dependent on the geometry of the object. The RMT method chosen to for DFAM was Selective Laser Melting (SLM) as it can ensure low porosity while manufacturing as compared to Direct electrode deposition and Electron Beam Melting. The CAD model was designed on Solidworks. The stress analysis was done on Ansys Workbench Static Structural while using a steady state thermal model.