In this paper, we give results for four optimization benchmark problems posed by the AIAA Aerodynamic Design Optimization Discussion Group. The benchmarks involve drag minimization for airfoils and wings, subject to geometric and aerodynamic constraints. Our design approach involves two forms of adaptation. First, the shape parameterization is gradually and automatically enriched from a coarse initial search space. Second, adjoint solutions are used to drive adaptive mesh refinement to control discretization error. The highest-resolution parameterizations and the finest, most accurate flow meshes are each used only when nearing the optimum, thus introducing greater complexity and accuracy only when necessary to further improve the design. This work demonstrates the ability of our shape optimization system to automatically solve representative aerodynamic design problems.
Case I Optimal Geometry (Tecplot, upper surface only)