@inproceedings{oai:jaxa.repo.nii.ac.jp:00005675,
 author = {丸山, 大悟 and 松島, 紀佐 and 楠瀬, 一洋 and 中橋, 和博 and Maruyama, Daigo and Matsushima, Kisa and Kusunose, Kazuhiro and Nakahashi, Kazuhiro},
 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 = {There is a biplane concept for an efficient supersonic flight. Busemann biplane is a representative airfoil which has possibility of realizing low-boom and low wave drag. Aerodynamic designs based on the Busemann biplane are demanded for future supersonic transports. In this paper, possibilities of designing supersonic biplanes by utilizing an inverse problem method are discussed based on Computational Fluid Dynamics (CFD). The inverse problem method which has been used in this paper is based on the theory of oblique shock wave. Therefore, it is necessary to examine its usefulness of designing airfoils which causes complicated phenomena such as biplanes where two airfoil elements interfere with each other and three-dimensional wings. We attempted two-dimensional cases in our current studies. It was confirmed that a certain biplane which differed from the Busemann biplane converged to the known Busemann biplane in 14 times iterations of design procedure. This knowledge is stated in the previous paper of this one. Then a practical biplane configuration was designed by utilizing the inverse problem method. After 14 times iterations, biplane configuration which has lower wave drag than a zero-thickness single flat plate airfoil at sufficient lift conditions has been successfully designed. Finally, applications to designing three-dimensional biplane wings are attempted. Target and initial geometries are set to the same ones as the case of two-dimensional. The above-mentioned inverse problem method was applied to total ten sections. In three-dimensional cases which have more complicated phenomena than two-dimensional cases such as disparity in flow of span direction, convergence after 14 times iterations was confirmed., 資料番号: AA0063824020, レポート番号: JAXA-SP-07-008E},
 pages = {195--205},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {Inverse design of biplane airfoils for efficient supersonic flight: Preliminary trial to construct biplane airfoil data base},
 volume = {JAXA-SP-07-008E},
 year = {2008}
}