Graduate School, Tokyo Metropolitan University
Aircraft Systems Research Group, Institute of Aeronautical Technology, Japan Aerospace Exploration Agency (JAXA)(APG)
Tokyo Metropolitan University
出版者
宇宙航空研究開発機構(JAXA)
出版者（英）
Japan Aerospace Exploration Agency (JAXA)
雑誌名
宇宙航空研究開発機構特別資料
雑誌名(英)
JAXA Special Publication: Proceedings of 44th Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2012
44th Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2012 (July 5-6, 2012. Toyama International Conference Center), Toyama Japan
抄録（英）
Multidisciplinary design optimization (MDO) is a practical key technology for the design of a supersonic transport (SST). The computational cost of MDO including aerodynamic design, however, should be expensive with high-fidelity CFD simulations. Therefore, surrogate models, such as response surface method or Kriging method are promising techniques for efficient MDO. Nevertheless, the computational cost will be still expensive to conduct the MDO using a surrogate model in practical time period because a lot of CFD calculations are required for global search. In this study, a fusion of the database with a low-cost/ low-fidelity solver and a high-cost/ high-fidelity solver in the Kriging model is considered to develop a more efficient global exploration method. A test problem with mathematical equation models and a practical aerodynamic design problem of a supersonic wing are carried out to investigate the efficiency of the proposed method. In t""" he supersonic wing design, a linear panel method and a structured Euler CFD solver are employed as a low-fidelity and a high-fidelity solver, respectively. As a result, the total computational cost is drastically reduced with the multi-fidelity method while the same optimum solutions can be explored as those with a single-fidelity optimization.
内容記述
形態: カラー図版あり
内容記述（英）
Physical characteristics: Original contains color illustrations
Kriging法を用いたMulti-Fidelity空力最適設計法の検討と超音速機主翼設計への適用
61958037.pdf
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