Multipoint Aerodynamic High Fidelity Shape Optimization of an Isolated Engine Nacelle

Abstract

The optimization of an isolated civil aircraft generic engine nacelle is presented in this paper using multi-point and up-to-date analysis and optimization tools. Opposite to components such as aircraft wing design, more limited material can be found on nacelle optimal aerodynamic design. The present work aims at describing a first step toward building a methodology complying with constraints which are specific to engine industrial design using high fidelity CFD approaches. Two critical design points, cruise and cross-wind, are considered separately and then concurrently using efficient local and global optimization algorithms.