@inproceedings{oai:jaxa.repo.nii.ac.jp:00037192,
 author = {柳原, 正明 and 重見, 仁 and 岡田, 典秋 and 室田, 勝一 and 水藤, 貴靖 and Yanagihara, Masaaki and Shigemi, Masashi and Okada, Noriaki and Murota, Katsuichi and Suito, Takanobu},
 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), 航空宇宙技術研究所と宇宙開発事業団が共同で実施したHOPE(H-2ロケット打上げ型有翼回収機)小型自動着陸実験(ALFLEX)ではデルタ翼チップフィン形態機の低速空力特性推定が目的の1つとして設定された。ここでは1996年にオーストラリアで実施された飛行試験から動的効果、地面効果も含めたALFLEX実験機の空力特性を推定し、事前に実施されたいくつかの風洞試験の結果と比較評価した。その結果、飛行試験による推定特性と、実験機の制御系設計に使用された基準風洞試験結果との差は概ねバリエーション内であったが、各種風洞試験の間にはかなりのばらつきが見られた。この差の原因としては模型支持方法、模型剛性、模型形状などの違いが考えられる。, For Automatic Landing Flight Experiment (ALFLEX) conducted jointly by NAL and NASDA using a scale model of HOPE (H-2 Orbiting Plane), the estimation of low-speed aerodynamic characteristics of the delta-wing tip-fin shaped model was aimed as one of the objects. In this report, based on the results of flight tests carried out in Australia 1996, aerodynamic characteristics including both dynamic and ground effects were estimated and compared with the previous results of wind tunnel tests. As a result, the differences were found among different kinds of wind tunnel test, in spite of having found a small difference, almost considered within the extent of variation, between the estimated characteristics from flight tests and the obtained results from tests of standard wind tunnel applied to the design of control system of experimental vehicle. The reason for these differences can be attributed to the difference of supporting method, rigidity, and shape of the model., 資料番号: AA0001434010, レポート番号: NAL SP-38},
 pages = {95--109},
 publisher = {航空宇宙技術研究所, National Aerospace Laboratory (NAL)},
 title = {ALFLEX実験機空力データベースの比較評価},
 volume = {38},
 year = {1998}
}