@inproceedings{oai:jaxa.repo.nii.ac.jp:00005761,
 author = {岩宮, 敏幸 and 吉田, 憲司 and 真保, 雄一 and 牧野, 好和 and 松島, 紀佐 and Iwamiya, Toshiyuki and Yoshida, Kenji and Shinbo, Yuichi and Makino, Yoshikazu 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ワークショップ.次世代超音速機の数値シミュレーション利用技術に関する国際ワークショップ 航空宇宙技術研究所 20000117-20000119 東京 日本, SST-CFD Workshop. International Workshops on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport National Aerospace Laboratory 20000117-20000119 Tokyo Japan, In the first stage of the NAL's experiment for supersonic transport (NEXST-1: Next generation Supersonic Transport-l) project, the aerodynamic design has focused on the of drag at a supersonic cruising speed with a clean wing-body configuration by using Computational Fluid Dynamics (CFD). In the course of design process, four aerodynamic concepts have been applied; (1) arrow-type planform design (2) warped wing (3) area-ruled body (4) a Natural Laminar Flow (NLF) wing. (1) and (2) are effective for the reduction of drag due to lift while (3) is effective the reduction of wave drag due to volume. They are the concepts based on the linear theory. The concept (4) is devised for the reduction of the friction drag. The application of the NLF concept to the SST (SuperSonic Transport) configuration has no previous instance and an original trial. For the realization of the NLF wing at supersonic cruising speed, we first designed a pressure distribution on the wing and then applied an inverse design method based on the supersonic small perturbation equation. After less than 10 design cycles, we obtained satisfactory design result which display a good agreement with target pressure. The transition position was evaluated by an incompressible boundary layer stability code (SALLY code) and compressible boundary layer stability code (LSTAB code), the latter of which was developed in NAL. The evaluation revealed that the turbulence transition characteristics are good., 資料番号: AA0063609030, レポート番号: JAXA-SP-06-029E},
 pages = {274--279},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {Aerodynamic design of supersonic experimental airplane},
 volume = {JAXA-SP-06-029E},
 year = {2007}
}