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Other TitleCurrent status of hypersonic boundary layer transition researches in the impulsive facility HIEST
Author(jpn)丹野, 英幸; 小室, 智幸; 佐藤, 和雄; 高橋, 政浩; 小寺, 正敏; 伊藤, 勝宏
Author(eng)Tanno, Hideyuki; Komuro, Tomoyuki; Sato, Kazuo; Takahashi, Masahiro; Kodera, Masatoshi; Ito, Katsuhiro
Author Affiliation(jpn)宇宙航空研究開発機構; 宇宙航空研究開発機構; 宇宙航空研究開発機構; 宇宙航空研究開発機構; 宇宙航空研究開発機構; 宇宙航空研究開発機構
Author Affiliation(eng)Japan Aerospace Exploration Agency (JAXA); Japan Aerospace Exploration Agency (JAXA); Japan Aerospace Exploration Agency (JAXA); Japan Aerospace Exploration Agency (JAXA); Japan Aerospace Exploration Agency (JAXA); Japan Aerospace Exploration Agency (JAXA)
Issue Date2009-12-28
PublisherJapan Aerospace Exploration Agency (JAXA)
Publication titleJAXA special publication: Proceedings of the Wind Technology Association 81st meeting
宇宙航空研究開発機構特別資料: 第81回風洞研究会議論文集
Publication date2009-12-28
AbstractWind tunnel experiments were performed to investigate hypersonic boundary layer transition in the impulsive facility HIEST. A 7 deg half-angle cone model 1100 mm long was designed and manufactured for the study. To change the Reynold's number, stagnation enthalpy was varied from H(sub 0) = 3.5 MJ/kg (Re = 6.0 x 10(exp 6) /m) to H(sub 0) = 8.7 MJ/kg (Re = 1.6 x 10(exp 6) /m). Seventy-two miniature co-axial thermocouples were flush-mounted on the surface of the model to measure heat flux distribution. Surface pressure fluctuation was measured in order to observe the second-mode instability in the boundary layer. The heat flux distribution measurement indicated that transition occurred on the model at approximately Re = 4.0 x 10(exp 6). Surface pressures exhibited peaks in their frequency spectra that were thought to represent second-mode instability. Schlieren high-speed video showed disturbances in the vicinity of the model surface at the location where laminar-turbulent transition occurred.
DescriptionOriginal contains color illustrations
Wind Tunnel Technology Association Meeting
形態: カラー図版あり
会議情報: 第81回風洞研究会議(2008年11月20日-11月21日)
KeywordsShock tunnel, Boundary layer transition, High-enthalpy flow
Document TypeConference Paper
JAXA Category特別資料
Report NoJAXA-SP-09-005

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