LAUSR

Abstract In this paper, a fully automated framework dedicated to the high-fidelity multidisciplinary design optimization of aircraft wing is developed. This design framework integrates a set of popular commercial software using their programming/scripting capabilities. It goes through geometric modeling in SIEMENS NX, aerodynamic meshing in ICEM CFD, flow solution using ANSYS FLUENT, structural finite element modeling in MSC.PATRAN and structural sizing in MSC.NASTRAN. By adopting a parametric modeling methodology, the structural and aerodynamic metrics reflecting the wing performance can be evaluated given a description of its shape and dimensions. In order to overcome the high cost of simulation models and allow the efficient solution of high-fidelity optimization problems, a surrogate-based optimization strategy is adopted. The reliability of the proposed approach is investigated through its application to the design of a high-speed passenger aircraft wing. The optimization objective is to maximize the aircraft range, given by the Breguet equation, while maintaining the lift coefficient and the structural safety. The case study results in a 8.9% increase in the range by considering shape and structural design variables.