Airfoil Parameterization and Optimization Based on the CST Method

This paper delves into the evolution of airfoils and the various design methods that have been utilized over time. The application of airfoils, which is crucial to aircraft design, pertains to the shaping of wings, compressors, and turbine blades, significantly impacting lift and drag forces. Historical developments in airfoil design have seen transitions from basic shapes to refined, mathematically defined profiles. This study particularly emphasizes the CST (Class function/Shape function Thickness distribution) Method as an advanced and efficient approach for airfoil generation and optimization. Using Python3 and the application Profili, different airfoil shapes are computed and evaluated through numerical simulations in COMSOL Multiphysics. The simulations aimed to optimize several performance characteristics such as the lift coefficient, pressure distribution, and maximum angle of attack. The results highlight the enhanced performance of the newly generated airfoil compared to traditional designs, with a noticeable increase in maximum lift coefficient and a smoother pressure profile. This research illustrates the potential of the CST method coupled with computational tools to innovate airfoil designs, offering significant improvements for future applications. Future work will focus on optimizing CST parameters for specific performance criteria, extending the versatility and efficiency of the airfoil design process.