Airfoil Shape Optimization for Improved Aerodynamics

This project focuses on the optimization of a custom airfoil by systematically analyzing the effects of camber percentage (2%– 6%), camber position (1– 6), and angle of attack (6°) while maintaining a fixed thickness of 12%. The primary objective is to maximize the lift- to-drag ratio (L/D) to enhance aerodynamic efficiency and stability. A parametric investigation was conducted using both unilabiate and bivariate analyses to evaluate the influence of individual and combined aerodynamic parameters on airfoil performance. To achieve this, XFOIL, a high- fidelity aerodynamic analysis tool, was integrated with MATLAB for automated batch processing, enabling efficient computation of lift coefficient (Cₗ), drag coefficient (C𝒹), and the corresponding L/D ratios. The parametric study revealed that variations in camber and its position significantly affect aerodynamic characteristics, offering critical insights for the design of optimized airfoils applicable to aircraft wings, UAVs, and wind turbine blades. In addition to parametric analysis, this study explores advanced optimization techniques, with a focus on evolutionary algorithms such as the Genetic Algorithm (GA). The GA framework was employed to systematically search for airfoil configurations that yield optimal L/D ratios by iteratively refining candidate solutions based on selection, crossover, and mutation operations. Future work will incorporate Reynolds number effects and validate the optimization results using computational fluid dynamics (CFD) simulations and experimental testing for enhanced accuracy and practical applicability