Influence of Winglets Design Parameters on Aerodynamic and Stability of a Blended Wing-Body Aircraft

Abstract The Blended Wing Body (BWB) aircraft is a non-conventional aerodynamic configuration that merges the fuselage and wings into a seamless structure, offering significant advantages in fuel efficiency, payload capacity, and aerodynamic efficiency. However, the absence of conventional tail units introduces aerodynamic and stability challenges that require careful design optimization. This study investigates the aerodynamic and static stability characteristics of a baseline BWB design from the European Distributed Multi-Disciplinary Design and Optimization (EU MOB) project. The analysis is performed using a mid-fidelity numerical tool based on the vortex lattice method, incorporating geometric and mass properties from previous studies. Aerodynamic curves and static stability derivatives are evaluated across a specific flight regime and compared with existing literature verifying the suitability of the used tool for preliminary aerodynamic and stability assessments. Subsequently, a parametric study is conducted to assess the effects of varying winglet design parameters, including height, sweep, cant, and toe angles, on aerodynamic efficiency and static stability characteristics. The results demonstrate that optimized winglet configurations can enhance lift-to-drag ratio and improve static stability characteristics without significantly increasing drag. These findings provide valuable insights into the role of winglets in improving BWB aircraft performance and contribute to the optimization of next-generation aerodynamic designs.