@inproceedings{oai:jaxa.repo.nii.ac.jp:00037194,
 author = {青木, 竹夫 and 鈴木, 弘一 and 中村, 正剛 and 若松, 逸雄 and 中野, 英一郎 and Aoki, Takeo and Suzuki, Koichi and Nakamura, Seigo and Wakamatsu, Itsuo and Nakano, Eiichiro},
 book = {航空宇宙技術研究所特別資料, Special Publication of National Aerospace Laboratory},
 month = {Jan},
 note = {22-23 May 1997 (58th). 27-28 Nov. 1997 (59th), 22-23 May 1997 (58th). 27-28 Nov. 1997 (59th), 宇宙往還技術試験機の空力係数誤差を設定する作業の一環として06HOPE(H-2ロケット打上げ型有翼回収機)模型による対応風洞試験に続き、07HOPE模型を使用して同じ方法で対応風洞試験を行った。06および07の対応風洞試験結果はCn(sub β)の差のピークでは3倍異なったが、この他の差は、ほぼ同じレベル・同じ傾向を示した。また、今回は新たな別の試験結果も加えて、試験結果間の差の縮小の可能性についても議論する。, As a part of work for setting aerodynamic coefficient errors of experimental vehicle for reusable space transportation, corresponding wind tunnel comparing test on 07HOPE (H-2 Orbiting Plane) model was carried out in the same manner as the preceding test on 06HOPE. The results of comparing tests on the 06 and 07HOPE model showed that the peak of difference of Cn(sub beta) of 07HOPE model is three times as large as that of 06, but other differences were roughly in the same level and tendency. Further in this time, adding other new test results, the possibility of diminishing differences among test results is discussed., 資料番号: AA0001434012, レポート番号: NAL SP-38},
 pages = {139--153},
 publisher = {航空宇宙技術研究所, National Aerospace Laboratory (NAL)},
 title = {07HOPE遷音速対応風洞試験},
 volume = {38},
 year = {1998}
}