JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
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title波状変形による超音速自然層流機首の設計
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
Publisher宇宙航空研究開発機構(JAXA)
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
VolumeJAXA-RR-13-008
Start page1
End page52
Publication date2013-12-31
Languagejpn
eng
Abstract基準形状に正弦波状,あるいは局在する波状の変形を加えることで,超音速自然層流機首を設計することを試みた.変形のパラメータだけでなく,一様流に関するパラメータも変化させ,最も自然層流効果の大きくなる形状を調査した.その結果,変形によって周方向と軸方向の圧力勾配比が減少すると,側面の境界層遷移を支配する横流れ不安定を抑制し自然層流効果をもたらすことがわかった.また,この圧力勾配比を小さくするには,圧力分布のピーク位置,すなわち圧力係数が負圧側で極大となる位置をトップラインとボトムラインで適切に配置することが重要であることがわかった.そして,そのような自然層流効果をもたらす変形形状の設計指針を獲得し,自然層流機首となる形状例が得られた.正弦波変形における自然層流効果は,実験的にも検証できた.一方,全抵抗の増加を抑制するには,局在波変形の方が有効であることが示された.
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
ISSN1349-1113
NCIDAA1192675X
SHI-NOAA0062064000
Report NoJAXA-RR-13-008
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/21007


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