@inproceedings{oai:jaxa.repo.nii.ac.jp:00037218,
 author = {重見, 仁 and 柳原, 正明 and 中安, 英彦 and 米田, 洋 and 本田, 直志 and 開沼, 史和 and 福井, 冨久男 and Shigemi, Masashi and Yanagihara, Masaaki and Nakayasu, Hidehiko and Yoneda, Hiroshi and Honda, Naoshi and Kainuma, Fumikazu and Fukui, Fukuo},
 book = {航空宇宙技術研究所特別資料, Special Publication of National Aerospace Laboratory},
 month = {Aug},
 note = {航空宇宙技術研究所　宇宙開発事業団 28 Feb. 1997 Sydney, National Aerospace Laboratory. National Space Development Agency of Japan 28 Feb. 1997 Sydney Australia, ALFLEX(小型自動着陸飛行実験)の飛翔体開発には、飛翔体の空力特性をできるだけ正確に見積る必要がある。これは搭載する制御システムの設計に不可欠だからである。このため、数種の異なる寸法の飛翔体模型を用いて6回の風洞試験を行い、さらに、開発の最終段階で、サブシステムの性能とその改良結果を確認するために2回の風洞試験を行った。合計8回の風洞試験は、3つの組織において4つの風洞を用いて行われ、この報告では、これら風洞試験結果から推定されるALFLEX飛翔体の空力特性を紹介した。, For the development of the ALFLEX (Automatic Landing Flight Experiment) vehicle, it was necessary to estimate its aerodynamic characteristics before as accurately as possible, since they were essential for the design of the control system loaded onboard. To meet this requirement, six wind tunnel tests were conducted using several models of different sizes. In addition, two wind tunnel tests were conducted in the final stage of development to confirm the performance of subsystems or to check the result of the improvement of a subsystem. In this paper, these eight wind tunnel tests made at three organizations employing four wind tunnels are introduced along with the aerodynamic characteristics of the ALFLEX vehicle estimated in those tests., 資料番号: AA0001565015, レポート番号: NAL SP-39T},
 pages = {145--152},
 publisher = {航空宇宙技術研究所, National Aerospace Laboratory (NAL)},
 title = {Wind tunnel tests for ALFLEX},
 volume = {39T},
 year = {1998}
}