@techreport{oai:jaxa.repo.nii.ac.jp:00041200,
 author = {重見, 仁 and 岩崎, 昭人 and 藤田, 敏美 and 大貫, 武 and 李家, 賢一 and 中安, 英彦 and 加納, 康臣 and Shigemi, Masashi and Iwasaki, Akihito and Fujita, Toshimi and Onuki, Takeshi and Rinoie, Kenichi and Nakayasu, Hidehiko and Kano, Yasuomi},
 month = {Nov},
 note = {HOPE(H-2ロケット打上げ型有翼回収機)小型自動着陸(ALFLEX)実験機設計のために必要となる空力データの取得を目的として、実験機の8.9％模型を用いた低速風洞試験を実施した。この実験の目的は次の5つである。(1)使用している簡易スティング支持方式が、一様流に及ぼす影響の解明。(2)機体に作用する6分力の測定。(3)舵面ヒンジモーメント測定。(4)機体周りの圧力分布測定。(5)機体周りの流れの状態の観測。得られたデータはALFLEX実験機基本設計を行なう上で、機体空力モデル作成と制御則の構築、舵面作動用アクチュエータの仕様決定、スピードブレーキの大きさ、形状の確認などを行なう際に用いられる。また、機体後部の剥離の様子を可視化すると同時に、境界層の遷移をモニタして、変化する流れの定性的なデータを取得した。, A low speed wind tunnel test was conducted for the 8.9 percent model of the ALFLEX (Automatic Landing FLight EXperiment) vehicle. The objectives of the experiment were (1) To clarify the effect of the makeshift sting support on the main flow; (2) to measure the forces and moments acting on the model; (3) to measure the hinge moments acting around the axes of control surfaces; (4) to measure the distribution of the static pressure on both sides of the wings; and (5) to observe the situation of the flow passing by the model. The data obtained in this wind tunnel test are utilized in the design of the ALFLEX vehicle. They are essential for designing the aerodynamic model of the vehicle, for determination of the necessary ability of the actuators which operate the control surfaces, for confirmation of the size and configuration of the speed brakes, and so on. The visualization of the separated flow at the rear part of the model was, along with the surveillance of the boundary layer transition by the hot films, helpful to understand the actual flow behavior of the model., 資料番号: AA0004230000, レポート番号: NAL TR-1215},
 title = {HOPE小型自動着陸実験機8.9％模型の低速風洞試験},
 year = {1993}
}