JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
62064000.pdf12.84 MB
Other TitleDesign of Natural Laminar Flow Nose for Supersonic Transport by Wavy Deformation
Author(jpn)徳川, 直子; 川井, 太朗; 戸塚, 絢子; 石川, 敬掲; 上田, 良稲
Author(eng)Tokugawa, Naoko; Kawai, Taro; Tozuka, Ayako; Ishikawa, Hiroaki; Ueda, Yoshine
Author Affiliation(jpn)宇宙航空研究開発機構航空本部機体システム研究グループ; ヤマハ発動機株式会社; キヤノン株式会社; 株式会社TOUA; 東京ビジネスサービス株式会社
Author Affiliation(eng)Aircraft Systems Research Group, Institute of Aeronautical Technology, Japan Aerospace Exploration Agency (JAXA); Yamaha Motor Co., Ltd.; Canon Inc.; TOUA Co. Ltd.; Tokyo Business Service Co. Ltd.
Issue Date2013-12-31
Japan Aerospace Exploration Agency (JAXA)
Publication title宇宙航空研究開発機構研究開発報告
JAXA research and development report
Start page1
End page52
Publication date2013-12-31
The transition characteristics were examined numerically on candidate shapes in order to design a natural laminar flow nose for a supersonic transport. Two types of deformation from a baseline shape were examined. One is sinusoidal type, and another is localized type. Not only parameters of geometry which define the deformation, but also the conditions of uniform flow were varied to obtain the largest effect of natural laminar flow. In results, the crossflow instability, which dominates the boundary-layer transition at the side area, was found to be suppressed from the small ratio of pressure gradients in azimuthal and axial directions at the side area. Moreover it was found that the relative location of bump in pressure distribution along leeward and windward rays is a key to yield small ratio of pressure gradient in azimuthal direction. The effect of natural laminar flow for sinusoidal deformation was confirmed experimentally. On the other hand, the localized deformation was found to be more effective in order to suppress increasing of total drag than the sinusoidal deformation.
Description形態: カラー図版あり
Physical characteristics: Original contains color illustrations
KeywordsDrag Reduction; Supersonic; Boundary-layer Transition; Natural Laminar Flow
Document TypeTechnical Report
JAXA Category研究開発報告
NASA Subject CategoryAerodynamics
Report NoJAXA-RR-13-008

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