In recent years, eVTOLs have emerged as a promising technological innovation in the field of urban air mobility, driven by the need for more sustainable, efficient, and versatile transportation solutions in densely populated areas. These aircraft offer a potential alternative to traditional ground transport, addressing urban congestion, reducing emissions, and providing faster, more flexible means of mobility. Their design, however, introduces new challenges. This project is centered on the design of a wing-tail configuration for an eVTOL aircraft, giving special attention to the interaction between both components, which plays a critical role in determining overall flight performance. The primary objective of the study is to determine the sizing, shaping, and positioning of the wing and the tail, assessing how the forces and moments generated by these components interact and affect the aircraft's behavior, while complying with the requirements given by ONAerospace. To achieve this, a preliminary design of both components has been carried out under free-stream conditions, focusing on their individual aerodynamic performance. Subsequently, an iterative process has been employed to analyze the combined lift and moment contributions, with special attention given to their impact on the aircraft's stability and ability to maintain a constant altitude. Computational tools such as SolidWorks have been used for geometric 3D modeling, while MATLAB has been employed to compute, refine, and plot the aerodynamic parameters. The results indicate that the wing design, based on empirical data, meets the expected lift production requirements across the specified flight conditions without needing design changes. The NACA 6412 airfoil utilized in the wing configuration contributes to stable lift production, eliminating the need for hyper-lift devices. The tail design, selected using volume coefficients, effectively balances the aircraft's moments. The achieved stability margin of 45.51% ensures that the aircraft remains stable and responsive, despite its prioritization of stability for medical applications. The aerodynamic efficiency, reflected by a lift-to-drag ratio between 10 and 13, is an acceptable value given the operational constraints. These results confirm that the final wing-tail design successfully meets the project's stability and performance criteria. However, future studies could further optimize efficiency by exploring alternative materials and conducting structural analyses.