@inproceedings{oai:jaxa.repo.nii.ac.jp:00004917,
 author = {丹野, 英幸 and 小室, 智幸 and 佐藤, 和雄 and 伊藤, 勝宏 and 藤井, 啓介 and Hideyuki, Tanno and Komuro, Tomoyuki and Sato, Kazuo and Ito, Katsuhiro and Fujii, Keisuke},
 book = {宇宙航空研究開発機構特別資料: 第41回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2009論文集, JAXA Special Publication: Proceedings fo 41st Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2009},
 month = {Feb},
 note = {平成21年6月18-19日. 宇宙航空研究開発機構調布航空宇宙センター, 18 June-19 June, 2009, Japan Aerospace Exploration Agency, Surface pressure measurement of a 7 deg half-angle cone model was conducted under hypersonic high-enthalpy flow condition. The measurement was performed in the impulsive facility HIEST. 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) = 8.2 MJ/kg (Re = 1.6 x 10(exp 6)/m). On the cone model, Eighty-six 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., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0064672019, レポート番号: JAXA-SP-09-011},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {極超音速境界層における表面圧力変動の計測},
 volume = {JAXA-SP-09-011},
 year = {2010}
}