In recent times, we have witnessed a significant evolution in the field of aviation that places strong emphasis on environmental sustainability. This evolution has given rise to a new generation of aircraft known as eVTOL (Electric Vertical Takeoff and Landing), which combine the efficiency of electricity with the versatility of vertical takeoff and landing. The future of urban transportation requires the development and regulation of these types of vehicles to reduce emissions, environmental impact, and alleviate congestion in densely populated areas. Consequently, many companies are developing eVTOL aircraft. ONAerospace is a startup with the primary goal of designing an eVTOL for medical assistance and rescue missions. This aircraft will combine the benefits of a helicopter for takeoffs and landings with those of a conventional airplane during the cruise phase. The aim is to provide a sustainable and efficient alternative to current rescue helicopters. In this project, the study will focus on the aerodynamic analysis and design of the ONAjet¿s main wing. The primary objective of the wing design is to provide a simple, practical, and efficient solution. Therefore, the most convenient approach will be assessed in each situation to avoid increasing the complexity of the aircraft¿s design and manufacturing in the future. Past studies and previous versions of the aircraft are highly relevant and provide key information for the ongoing development of the ONAjet. Compared to the old ONAjet, the goal is to reduce the wing¿s chord length and wing area. Additionally, the previous wing profile will be compared to new alternatives to find a more efficient option for the requirements of the new version of the aircraft. The methodology followed during the wing design has been carried out following the steps outlined in various aircraft design books. To analyze different wing parameters and obtain an appropriate comparison, XFLR5 and OpenVSP software programs have been used. Subsequently, the most relevant validation has been done using ANSYS, through a 2D simplified Computational Fluid Dynamics (CFD) analysis. Finally, the final three-dimensional wing design has been developed using SolidWorks. As a final result, a high-wing configuration with a 4¿anhedral angle, a taper ratio of 0.7, a wingspan of 10 meters and an average aerodynamic chord of 0.96 meters has been selected. The required lift has been successfully generated, taking into account that the aircraft also counts with rotors contributing to lift generation. However, further detailed studies will be required to integrate the wing with the aircraft¿s propulsion systems to evaluate the interference effects.

Objectius de Desenvolupament Sostenible::17 - Aliança per a Aconseguir els Objetius

Objectius de Desenvolupament Sostenible::7 - Energia Assequible i No Contaminant