@inproceedings{oai:jaxa.repo.nii.ac.jp:00005156,
 author = {丹野, 英幸 and 小室, 智幸 and 佐藤, 和雄 and 高橋, 政浩 and 小寺, 正敏 and 伊藤, 勝宏 and Tanno, Hideyuki and Komuro, Tomoyuki and Sato, Kazuo and Takahashi, Masahiro and Kodera, Masatoshi and Ito, Katsuhiro},
 book = {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, JAXA Special Publication: Proceedings of the Wind Technology Association 81st meeting},
 month = {Dec},
 note = {第81回風洞研究会議(2008年11月20日-11月21日）, Wind 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., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, Wind Tunnel Technology Association Meeting, 資料番号: AA0064475004, レポート番号: JAXA-SP-09-005},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {高温衝突風洞HIESTにおける極超音速境界遷移研究について},
 volume = {JAXA-SP-09-005},
 year = {2009}
}