A Parametric Approach to Supercritical Airfoil Design Optimization
Jacob Courtney Haderlie, William Crossley · 9th AIAA Aviation Technology, Integration, and Operations Conference (ATIO) · 2009
Supercritical airfoil design optimization is performed employing Kulfan’s class function shape function transformation (CST) technique to represent the airfoil shape and Design of Experiments (DOE) trials to build response surfaces for approximate optimization. The CST parameterization eectively reduces the number of design variables needed for design optimization of complex geometry. Surrogate models, i.e., response surfaces, approximate the results of a high-delity Computational Fluid Dynamics (CFD) analysis program. Using these surrogate models, a multi-point optimization problem seeks to minimize drag while providing a required amount of lift and pitching moment at three transonic Mach numbers. The advantages and disadvantages of surrogate model-based optimization for this application are discussed.