{"created":"2023-06-20T15:11:31.363509+00:00","id":41200,"links":{},"metadata":{"_buckets":{"deposit":"e0d96da1-9fc4-4e1c-9a5c-5504eeff8f0d"},"_deposit":{"created_by":1,"id":"41200","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"41200"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00041200","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["451138","451140","451141","451132","451135","451134","451131","451130","451139","451136","451143","451142","451133","451137"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Low speed wind tunnel test for 8.9 percent model of HOPE ALFLEX vehicle"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1993-11","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"23","bibliographicPageStart":"1","bibliographicVolumeNumber":"1215","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所報告"},{"bibliographic_title":"Technical Report of National Aerospace Laboratory","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"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。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"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.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0004230000","subitem_description_type":"Other"}]},"item_3_description_33":{"attribute_name":"レポート番号","attribute_value_mlt":[{"subitem_description":"レポート番号: NAL TR-1215","subitem_description_type":"Other"}]},"item_3_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"航空宇宙技術研究所"}]},"item_3_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"National Aerospace Laboratory (NAL)"}]},"item_3_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"0389-4010","subitem_source_identifier_type":"ISSN"}]},"item_3_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"航空宇宙技術研究所 新型航空機研究グループ"},{"subitem_text_value":"航空宇宙技術研究所 新型航空機研究グループ"},{"subitem_text_value":"航空宇宙技術研究所 新型航空機研究グループ"},{"subitem_text_value":"航空宇宙技術研究所 新型航空機研究グループ"},{"subitem_text_value":"航空宇宙技術研究所 新型航空機研究グループ"},{"subitem_text_value":"宇宙開発事業団"},{"subitem_text_value":"宇宙開発事業団"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Advanced Aircraft Research Group"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Advanced Aircraft Research Group"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Advanced Aircraft Research Group"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Advanced Aircraft Research Group"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Advanced Aircraft Research Group"},{"subitem_text_language":"en","subitem_text_value":"National Space Development Agency of Japan"},{"subitem_text_language":"en","subitem_text_value":"National Space Development Agency of Japan"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"重見, 仁"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"岩崎, 昭人"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"藤田, 敏美"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"大貫, 武"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"李家, 賢一"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"中安, 英彦"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"加納, 康臣"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Shigemi, Masashi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Iwasaki, Akihito","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Fujita, Toshimi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Onuki, Takeshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Rinoie, Kenichi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Nakayasu, Hidehiko","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Kano, Yasuomi","creatorNameLang":"en"}],"nameIdentifiers":[{}]}]},"item_files":{"attribute_name":"ファイル情報","attribute_type":"file","attribute_value_mlt":[{"accessrole":"open_date","date":[{"dateType":"Available","dateValue":"2020-01-27"}],"displaytype":"detail","filename":"naltr01215.pdf","filesize":[{"value":"3.3 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr01215.pdf","url":"https://jaxa.repo.nii.ac.jp/record/41200/files/naltr01215.pdf"},"version_id":"f47cb2b8-9ec4-47d9-a182-743f753d21f7"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"HOPE","subitem_subject_scheme":"Other"},{"subitem_subject":"H-2ロケット打上げ型有翼回収機","subitem_subject_scheme":"Other"},{"subitem_subject":"自動着陸","subitem_subject_scheme":"Other"},{"subitem_subject":"飛行実験","subitem_subject_scheme":"Other"},{"subitem_subject":"低速風洞試験","subitem_subject_scheme":"Other"},{"subitem_subject":"風洞模型支持","subitem_subject_scheme":"Other"},{"subitem_subject":"模型支持干渉","subitem_subject_scheme":"Other"},{"subitem_subject":"ヒンジモーメント計測","subitem_subject_scheme":"Other"},{"subitem_subject":"静圧分布計測","subitem_subject_scheme":"Other"},{"subitem_subject":"宇宙往還機","subitem_subject_scheme":"Other"},{"subitem_subject":"空力特性","subitem_subject_scheme":"Other"},{"subitem_subject":"風洞吹き上げ角計測","subitem_subject_scheme":"Other"},{"subitem_subject":"レイノルズ数効果","subitem_subject_scheme":"Other"},{"subitem_subject":"流れ剥離","subitem_subject_scheme":"Other"},{"subitem_subject":"流れの可視化","subitem_subject_scheme":"Other"},{"subitem_subject":"HOPE","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"H 2 orbiting plane","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"automatic landing","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flight experiment","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"low speed wind tunnel test","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wind tunnel model support","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"model support interference","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"hinge moment measurement","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"static pressure distribution measurement","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"spaceplane","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamic characteristic","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wind tunnel upflow measurement","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Reynolds number effect","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flow separation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flow visualization","subitem_subject_language":"en","subitem_subject_scheme":"Other"}]},"item_language":{"attribute_name":"言語","attribute_value_mlt":[{"subitem_language":"jpn"}]},"item_resource_type":{"attribute_name":"資源タイプ","attribute_value_mlt":[{"resourcetype":"technical report","resourceuri":"http://purl.org/coar/resource_type/c_18gh"}]},"item_title":"HOPE小型自動着陸実験機8.9％模型の低速風洞試験","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"HOPE小型自動着陸実験機8.9％模型の低速風洞試験"}]},"item_type_id":"3","owner":"1","path":["1893","1917"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"41200","relation_version_is_last":true,"title":["HOPE小型自動着陸実験機8.9％模型の低速風洞試験"],"weko_creator_id":"1","weko_shared_id":1},"updated":"2023-06-20T19:12:13.787801+00:00"}