@inproceedings{oai:jaxa.repo.nii.ac.jp:00037391,
 author = {丹羽, 宏明 and 齊藤, 勝也 and 中野, 英一郎 and 青木, 竹夫 and 横幕, 良生 and Niwa, Hiroaki and Saito, Katsuya and Nakano, Eiichiro and Aoki, Takeo and Yokomaku, Yoshio},
 book = {航空宇宙技術研究所特別資料, Special Publication of National Aerospace Laboratory},
 month = {May},
 note = {21-22 May 1998 (60th). 26-27 Nov. 1998 (61st), 21-22 May 1998 (60th). 26-27 Nov. 1998 (61st), HOPE-X(宇宙往還技術試験機)の実レイノルズ数付近における空力特性データを取得する為に、5%HOPE(H-2ロケット打ち上げ型有翼回収機)風洞試験模型を製作し、マッハ数0.4〜1.3の風洞試験をETW(欧州遷音速風洞株式会社)で実施した。本レポートは、極低温高レイノルズ数風洞試験用模型の特徴、日本から初めて利用したETW試験設備およびレイノルズ数効果を含めた試験結果について概要を紹介する。また、他風洞試験およびCFD(数値流体力学)解析との結果比較、風洞試験間の誤差について述べる。, A five percent model of HOPE (H-2 Orbiting Plane) was made to obtain the aerodynamic characteristics data near actual Reynolds number for HOPE-X (H-2 Orbiting Plane Experimental), and a wind tunnel test at Mach numbers in the range between 0.4 and 1.3 was conducted at European Transonic Windtunnel GmbH (ETW) in Germany. In this paper, the characteristics of the model for cryogenic high Reynolds number wind tunnel, the outline of test facilities of ETW, which a Japanese team utilized for the first time, and some test results including the Reynolds number effect are reported. These results were compared with those previously obtained in other wind tunnels and those of CFD (Computational Fluid Dynamics) analysis, and the errors between different wind tunnels were discussed., 資料番号: AA0001959011, レポート番号: NAL SP-42},
 pages = {111--131},
 publisher = {航空宇宙技術研究所, National Aerospace Laboratory (NAL)},
 title = {HOPE極低温高レイノルズ数風洞試験について},
 volume = {42},
 year = {1999}
}