@inproceedings{oai:jaxa.repo.nii.ac.jp:00014331,
 author = {丹野, 英幸 and 小室, 智幸 and 佐藤, 和雄 and 伊藤, 勝宏 and Hideyuki, Tanno and Komuro, Tomoyuki and Sato, Kazuo and Ito, Katsuhiro},
 book = {宇宙航行の力学シンポジウム: 平成22年度, Symposium on Flight Mechanics and Astrodynamics: 2010},
 month = {Aug},
 note = {宇宙航行の力学シンポジウム 平成22年度 (2010年12月16-17日. 宇宙航空研究開発機構宇宙科学研究所), 相模原市, 神奈川県, Symposium on Flight Mechanics and Astrodynamics,  2010 (December 16-17, 2010. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS)), Sagamihara, Kanagawa Japan, Aeroheating test with re-entry capsule configuration has carried out in JAXA-HlEST. An Apollo CM 6% scale model has applied in the test, which model has used in the previous test campaign conducted in FY2009. The model has 84 fast-response coaxial thermocouples on the windward to measure the heat flux distribution. Twelve thermocouples and two Piezo-resistive pressure transducers were also mounted on the aft of the model and were used to determine flow establishment around the model. In the present test campaign abnormally high heat-flux phenomenon was focused, which phenomenon was observed under stagnation enthalpy H(sub 0) over 17 MJ/kg and stagnation pressure P(sub 0) over 45MPa in the last test campaign. To see any effects on the phenomenon causing from high-temperature chemical reaction, air and pure nitrogen were applied as test gas. Stagnation enthalpy and stagnation pressure were varied from H(sub 0)=3MJ/kg to 21MJ/kg, and from P(sub 0)=30MPa to 65MPa, respectively. The unit Reynolds number under the condition was 0.9 million/m to 4.5 million/m. Aeroheating characteristics were observed at model angle of attack 0 degree with fully laminar or with transitional boundary layer. Measured heat flux was normalized by the products of the Stanton number and the square-root of the Reynolds number for correlation with other wind tunnel results. The measurement showed that the normalized heat flux increase as stagnation enthalpy. Besides, no remarkable difference was observed between air test gas and pure nitrogen test gas, which results implied the chemical reactions had no or minor effects on the anomalies., 資料番号: AA0065106012},
 publisher = {宇宙航空研究開発機構宇宙科学研究所, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)},
 title = {高エンタルピ・高圧気流条件での再突入カプセルの風洞実験},
 year = {2011}
}