Geometrically consistent aerodynamic optimization using an isogeometric Discontinuous Galerkin method

The objective of the current work is to define a design optimization methodology in aerodynamics, which all numerical components are based on unique geometrical representation, consistent with Computer-Aided Design (CAD) standards. In particular, parameterized by Non-Uniform Rational B-Splines (NURBS), computational domain automatically constructed using rational Bézier elements extracted from NURBS boundaries without any approximation and resolution flow equations relies an adaptive Discontinuous Galerkin (DG) method representations. A Bayesian framework used optimize control points, single- or multi-objective, constrained, global framework. resulting therefore fully CAD-consistent, high-order space time, includes local adaption shock capturing capabilities, exhibits high parallelization performance. proposed methods described details their properties established. Finally, two problems provided as illustrations: shape airfoil transonic regime, for drag reduction lift constraint, multi-objective law morphing subsonic regarding time-averaged lift, minimum instantaneous energy consumption.