@inproceedings{oai:jaxa.repo.nii.ac.jp:00005741,
 author = {真保, 雄一 and 吉田, 憲司 and 岩宮, 敏幸 and 高木, 亮治 and 松島, 紀佐 and Shinbo, Yuichi and Yoshida, Kenji and Iwamiya, Toshiyuki and Takaki, Ryoji and Matsushima, Kisa},
 book = {宇宙航空研究開発機構特別資料, JAXA Special Publication: Proceedings of International Workshops on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport (SST-CFD Workshop)},
 month = {Mar},
 note = {SST-CFD Workshop. International CFD Workshops for Super-sonic Transport Design 航空宇宙技術研究所 19980316-19980317 東京 日本, SST-CFD Workshop. International CFD Workshops for Super-sonic Transport Design National Aerospace Laboratory 19980316-19980317 Tokyo Japan, As a part of the NAL's scaled supersonic experimental airplane program to establish an aerodynamic design system based on Computational Fluid Dynamics (CFD), an aerodynamic configuration with no propulsion system was designed in a two-stage process. First, a baseline configuration was designed using a conventional linear theory. Then, the CFD and a supersonic inverse method were used to refine the wing geometry and to achieve a higher lift-to-drag ratio at a design point of M = 2 and CL = 0.1. A non-linear effect such as body to wind interference and a wing thickness effect were also handled in this phase. By making use of the inverse method, an upper surface of the wing was designed aiming at a natural laminar flow with a flat-type pressure distribution to reduce a friction drag. A wing warp was also adjusted to achieve an optimal load distribution designed by the linear theory to reduce a pressure drag. The designed new wing was evaluated by a Navier-Stokes analysis and an incompressible boundary layer stability code (SALLY code) and was found to have an improved lift-to-drag ratio, with a wider laminar flow regime and smaller friction drag than the initial geometry. Finally, the CFD analysis was compared with supersonic wind tunnel data and was found to be a well validated tool to be used in the design., 資料番号: AA0063609010, レポート番号: JAXA-SP-06-029E},
 pages = {67--72},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {Aerodynamic design of the scaled supersonic experimental airplane},
 volume = {JAXA-SP-06-029E},
 year = {2007}
}