Aerodynamic Optimization of Integrated Wing-Engine Geometry Using an Unstructured Vorticity Solver

摘要

This paper discusses the use of a high fidelity surface vorticity solver in conjunction with an optimizer to find optimal solutions for engine integration. The case study for this paper is an aerodynamically optimized engine configuration added to the DLR-F4 from the AIAA CFD drag prediction workshop. The unstructured meshes generated during the optimization process are produced by Open Vehicle Sketch Pad. The SwarmOps particle swarm optimization algorithm is used within Phoenix Integration Model Center during the optimization process.