Minimize the aerodynamic effect of a strut on the wing

Abstract

The field of aircraft design is continuously advancing through the utilization of scientific techniques and empirical methods. The incorporation of computational methods has facilitated the design process of new and complex aircraft, enabling more efficient conceptual design and optimization. These advancements have the potential to significantly reduce fuel consumption and emissions, making a positive impact on the environment, a critical global concern. The development of battery-electric airplanes represents a significant step towards creating a more sustainable aviation sector. Among the various emerging concepts, the Strut-Braced Wing (SBW) has shown great promise in enhancing aerodynamic efficiency while reducing wing weight.

However, the implementation of new concepts and technologies also presents new challenges and limitations that must be addressed, particularly the impact of aerodynamics on the aircraft’s range, which can impose limitations on its maximum travel distance. The primary objective of this thesis is to minimize the aerodynamiceffects of a strut and wing configuration by reducing total drag and increasing the Oswald efficiency of the Strut-Braced Wing during the conceptual design phase.

To achieve this goal, Sequential Quadratic Programming (SQP) and Genetic Algorithm (GA) optimization algorithms are employed, utilizing low-fidelity Computational Fluid Dynamics (CFD) methods. The airfoil data utilized in the study is obtained from the XFOIL tool, which provides important viscous aerodynamic characteristics.

By implementing these methodologies, it is anticipated that the aerodynamic performance of the Strut-Braced Wing configuration can be optimized, leading to improved efficiency and weight reduction. The results obtained from this research will contribute to the advancement of aircraft design and promote the development of more environmentally friendly and efficient aircraft during the conceptual design phase.