Aeropropulsive Shape Optimization of an Airfoil System in the Transonic Regime

Boundary-layer ingestion and distributed propulsion are important concepts for future aircraft systems and technologies. Both concepts have the potential to increase aerodynamic efficiency and improve aircraft design in various other ways. The present study aims to address design implications and challenges of configuring a highly integrated and distributed propulsion system into wing sections within the compressible flow environment, which is the aerodynamic regime associated with large, commercial transport aircraft. To this end, a design and optimization framework was established to facilitate two-dimensional aeropropulsive optimization with strict, complex geometric constraints. A bi-objective, multipoint aeropropulsive shape optimization problem was solved using this package for an underwing-propulsor airfoil system to demonstrate the performance improvements achievable for a highly integrated aeropropulsive system. The results of this optimization indicate that an aerodynamic drag reduction of 11% and required mechanical flow power reduction of 35% are achievable relative to a baseline configuration.