Diskret-Adjungierter aerodynamischer Formoptimierungsprozess am Beispiel eines getrimmten Transportflugzeugs mit aktivem Triebwerk

Kurzfassung

Shape optimization of a flying aircraft in self-propelled, trimmed conditions requires augmentation of the baseline aerodynamic shape-optimization problem by additional constraints for the steady-state equilibrium flight. To aerodynamically evaluate such design scenarios, additional numerical ingredients that are beyond the baseline CFD method come into play. The first part of the presentation is dedicated to the computational process chain required for a gradient-based shape optimization of a self-propelled, trimmed aircraft configuration. The backbone of the process is the HPC-platform FlowSimulator, allowing for an in-memory data exchange between the involved primal and dual tools without file I/O. In the second part, the process chain is applied to minimize the drag of a simplified two-dimensional aircraft model in combination with two different means of enforcing the trim constraints. Subsequently, a generic three-dimensional transport aircraft with active engines is optimized for minimum drag in trimmed transonic cruise conditions.