@inproceedings{oai:jaxa.repo.nii.ac.jp:00005674,
 author = {松島, 紀佐 and 丸山, 大悟 and 松澤, 拓未 and Matsushima, Kisa and Maruyama, Daigo and Matsuzawa, Takumi},
 book = {宇宙航空研究開発機構特別資料, JAXA Special Publication: Proceedings of Lectures and Workshop International: Recent Advances in Multidisciplinary Technology and Modeling},
 month = {Feb},
 note = {For the aerodynamic wing design, the superior points of a inverse problem method are discussed as well as two mathematical models each of which is the core equation of each inverse problem are introduces. One mathematical model comes from three-dimensional potential flow equation and he thin wing theory, while the other is led from Busemann's second order approximation based on the theory of oblique shock wave. The former yields the set of integral-differential equations and the latter does a quadratic equation in the corresponding inverse problem. Combining each inverse problem with residual-correction methodology and modern computational technology enables us to construct a low-cost and high-fidelity design method. To examine its capability and usefulness, several design problems have been done. Successful high-fidelity design results have been obtained for all cases. The computational cost is small. The inverse design needs about 20 time flow simulations which is much less than the cost of a general optimization., 資料番号: AA0063824019, レポート番号: JAXA-SP-07-008E},
 pages = {185--194},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {Numerical modeling for supersonic flow analysis and inverse design},
 volume = {JAXA-SP-07-008E},
 year = {2008}
}