Taguchi optimization and CFD analysis for Bezier-based airfoil geometry
Guneyhan Taskaya, Beytullah Erdogan
article (Uluslararası, Hakemli) | Yazar(lar): Guneyhan Taskaya, Beytullah Erdogan | Yıl: 2026 | Dergi/Kurum: AEROSPACE SCIENCE AND TECHNOLOGY | İndeks: WOS.SCI | DOI: 10.1016/j.ast.2026.111655 | Anahtar Kelimeler: Bezier curve, Taguchi, Lift coefficient, Drag coefficient, Airfoil — Özet: In this study, a new airfoil co
In this study, a new airfoil consisting of 16 control points, 8 each on the upper and lower curves of the airfoil geometry, was designed by modeling the Bezier curve with the MATLAB program. The Taguchi Method, which provides an effective and systematic approach in determining the optimum parameter combinations, was preferred in order to evaluate the effects of the parameters affecting the airfoil performance. Within the scope of the Design of Experiments (DOE) methodology, the analyses were conducted at a Reynolds number of Re=200,000 and an angle of attack of 8 degrees. The aim is to determine the optimal design conditions (maximum camber, maximum camber position, maximum thickness, leading edge radius, and trailing edge thickness) by considering five factors consisting of control points representing five basic parameters and to offer a highperformance original airfoil profile that can be used in general aerodynamic systems (Re=175,000-500, 000 Reynolds number and 0 degrees-21 degrees angle of attack). In this direction, the data obtained from Computational Fluid Dynamics (CFD) simulations based on the Taguchi L16 orthogonal array were statistically evaluated using Analysis of Variance (ANOVA). The performance ratio (CL/CD) of the new airfoil, obtained as a result of parametric studies on the optimum experimental parameter combination determined by the Taguchi method, was compared with the NACA 0012, NACA 6412, and NASA 747A315 airfoils, which are frequently used in the literature, and with 16 other configurations included in the analysis. The new airfoil, obtained with Bezier curves, shows that it provides approximately 32% performance improvement compared to the NASA 747A315 airfoil, approximately 13% compared to the NACA 6412 airfoil, and approximately 20% compared to the NACA 0012 airfoil.