Aerodynamic Design Optimization: Physics-Based Surrogate Approaches for Airfoil and Wing Design
The aerodynamic optimization community has recently started an effort to develop benchmark problems suitable for exercising aerodynamic optimization methods in a constrained design space. In the first round, four problems have been developed, two involving two-dimensional airfoils and the other two three-dimensional wings. In this paper, we address the two-dimensional problems which involve optimization of the NACA 0012 in inviscid transonic flow, as well as optimization of the RAE 2822 in viscous transonic flow. We solve the problems using a computationally efficient physics-based surrogate approach exploiting space mapping. Our results indicate that by shifting the computational burden to fast low-fidelity models, significant performance improvements can be achieved at the cost of a few evaluations of the expensive computational fluid dynamic models. In our approach, a commercial package FLUENT is used as the high-fidelity fluid flow solver with a hyperbolic C-mesh, whereas the versatile viscous-inviscid solver MSES is utilized as the low-fidelity model. The PARSEC parameterization method is used to describe the airfoil shapes with up to 10 design variables.
L. Leifsson et al., "Aerodynamic Design Optimization: Physics-Based Surrogate Approaches for Airfoil and Wing Design," Proceedings of the 52nd Aerospace Sciences Meeting (2014, National Harbor, MD), American Institute of Aeronautics and Astronautics (AIAA), Jan 2014.
The definitive version is available at https://doi.org/10.2514/6.2014-0572
52nd Aerospace Sciences Meeting (2014: Jan. 13-17, National Harbor, MD)
Mechanical and Aerospace Engineering
Center for High Performance Computing Research
Article - Conference proceedings
© 2014 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.
01 Jan 2014