@inproceedings{oai:jaxa.repo.nii.ac.jp:00005743,
 author = {松島, 紀佐 and 岩宮, 敏幸 and Jeong, Shinkyu and 大林, 茂 and Matsushima, Kisa and Iwamiya, Toshiyuki and Jeong, Shinkyu and Obayashi, Shigeru},
 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, Aerodynamic shape of a wing for NAL's SST (SuperSonic Transport) has been designed by a supersonic inverse design method. This method handles SST's wing-fuselage configurations and provides wing section's geometry at every span. The design system consists of a new inverse problem solver and a Navier-Stokes simulation. The design procedure is iterative; the baseline shape is Successively modified as the process of the inverse problem solver and Navier-Stokes simulation is iterated until the pressure distribution given by the designed wing can be regarded to converge to the target one. The design target is a NLF (Natural Laminar Flow) wing for the wing-fuselage combination at the speed of M(sub infinity) = 2.0. Several design constraints have been intended to be satisfied. By means of the method, a better wing shape which has much more desirable characteristics has been designed than that by the traditional linear theory., 資料番号: AA0063609012, レポート番号: JAXA-SP-06-029E},
 pages = {78--83},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {Aerodynamic wing design for NAL's SST using iterative inverse approach},
 volume = {JAXA-SP-06-029E},
 year = {2007}
}