Aerostructural Design Exploration of a Wing in Transonic Flow

摘要: Multidisciplinary design optimization (MDO) has been previously applied to aerostructural wing problems with great success. Most previous applications involve fine-tuning a well-designed aircraft wing. In this work, we broaden the scope of problem by exploring space optimization. We start rectangular and optimize aerodynamic shape sizing internal structure achieve minimum fuel burn on transonic cruise mission. use multi-level procedure decrease computational cost 40%. demonstrate that can transform into swept, tapered typical aircraft. The optimizer converges same when starting from different initial design. Additionally, separation constraint at low-speed, high-lift condition improve off-design performance optimized results in substantially better low-speed only slight performance.