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titleAerodynamic design of the scaled supersonic experimental airplane
Other TitleAerodynamic design of the scaled supersonic experimental airplane
Author(jpn)真保 雄一; 吉田 憲司; 岩宮 敏幸; 高木 亮治; 松島 紀佐
Author(eng)Shinbo, Yuichi; Yoshida, Kenji; Iwamiya, Toshiyuki; Takaki, Ryoji; Matsushima, Kisa
Author Affiliation(jpn)航空宇宙技術研究所; 航空宇宙技術研究所; 航空宇宙技術研究所 数理解析部; 航空宇宙技術研究所 数理解析部; 富士通 スーパーコンピューターシステムエンジニアリング統括部
Author Affiliation(eng)National Aerospace Laboratory; National Aerospace Laboratory; National Aerospace Laboratory Computational Sciences Division; National Aerospace Laboratory Computational Sciences Division; Fujitsu Ltd. Supercomputer System Engineering Division
Issue Date2007-03-30
PublisherJapan Aerospace Exploration Agency (JAXA)
宇宙航空研究開発機構
Publication titleProceedings of International Workshops on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport (SST-CFD Workshop)
Proceedings of International Workshops on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport (SST-CFD Workshop)
Start page67
End page72
Publication date2007-03-30
Languageeng
AbstractAs 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.
DescriptionJAXA Special Publication
宇宙航空研究開発機構特別資料
Keywordssupersonic aircraft; aircraft design; aerodynamic characteristic; computational fluid dynamics; lift drag ratio; planform; Mach number; arrow wing; aspect ratio; friction drag; pressure drag; 超音速機; 航空機設計; 空力特性; 計算流体力学; 揚抗比; 平面形; マッハ数; アロー翼; アスペクト比; 摩擦抗力; 圧力抗力
Document TypeConference Paper
JAXA Category特別資料
ISSN1349-113X
SHI-NOAA0063609010
Report NoJAXA-SP-06-029E
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/26863


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