{"created":"2023-06-20T15:10:12.687100+00:00","id":39806,"links":{},"metadata":{"_buckets":{"deposit":"bb16c64e-cc3b-41ad-9e87-91bbbe4d7d85"},"_deposit":{"created_by":1,"id":"39806","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"39806"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00039806","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["444550","444557","444558","444555","444554","444559","444553","444552","444549","444556","444551","444548"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Supersonic tests of the aerodynamic characteristics of the orbital reentry experiment vehicle model"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1996-07","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"30","bibliographicPageStart":"1","bibliographicVolumeNumber":"1300","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":"半頂角50度の球面鈍頭円錐形状の軌道再突入実験機が大気圏に再突入する時の空力特性を得るため、航技研の1m×1m超音速風洞を用いてマッハ数1.4≦M(sub ∞)≦4.0の範囲で軌道再突入実験模型およびその変形状模型について3分力試験を行った結果次のことが分かった。このような鍋形の鈍頭物体模型には静的には迎角を0度に復元するモーメント(風見安定)が作用する。また、抗力係数が垂直力係数に比べて大きいために負の揚力傾斜を示す。模型の肩の曲率半径の違いによる空力特性への影響は、低超音速域においてみられる。肩の曲率半径が小さい模型の抗力係数および縦揺れモーメント係数の絶対値の方が、肩の曲率半径が大きい模型の値より大きい。M(sub ∞)＝3.0付近を境にして空力係数の迎角に対する傾向が変化する。模型表面の流れの可視化によると、球面部と円錐部のつなぎ目で、流れに層流遷移バブルあるいは小さな剥離バブルが発生しているように観察される。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"To obtain the aerodynamic characteristics of the Orbital Reentry Experiment Vehicle (OREX), measurements of three force components of the OREX model and other modified models were carried out in the NAL supersonic wind tunnel (1 m x 1 m test cross-section) in the Mach number range where M(sub infinity) is greater than or equal to 1.4 and less than or equal to 4.0. The models have spherically blunted nose heads with the same radius. The effects of conical afterbody of 50 degree and 45 degree half-apex conical angles and four different radii of circumferential edges of 0 mm, 2 mm, 3.3 mm (OREX) and 10 mm were tested. The tests show that the models are statically stable for the pitching movement (vane-stable). The model with the edge of 3.3 mm shows larger recovering pitching moment than other models in low Mach number regions. The model with a sharp edge shows a larger drag coefficient than the one with a blunted edge.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0000594000","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-1300","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 空気力学部"},{"subitem_text_value":"航空宇宙技術研究所 空気力学部"},{"subitem_text_value":"航空宇宙技術研究所 空気力学部"},{"subitem_text_value":"航空宇宙技術研究所 空気力学部"},{"subitem_text_value":"航空宇宙技術研究所 空気力学部"},{"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 Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aerodynamics Division"},{"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":"野田, 順一"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"楯, 篤志"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"渡辺, 光則"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"関根, 英夫"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"吉永, 崇"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"秋元, 敏男"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Noda, Junichi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Tate, Atsushi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Watanabe, Mitsunori","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Sekine, Hideo","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Yoshinaga, Takashi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Akimoto, Toshio","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":"naltr01300.pdf","filesize":[{"value":"3.2 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr01300.pdf","url":"https://jaxa.repo.nii.ac.jp/record/39806/files/naltr01300.pdf"},"version_id":"fe054cbe-750d-4135-a9b0-16350e9da345"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"OREX","subitem_subject_scheme":"Other"},{"subitem_subject":"軌道再突入実験機","subitem_subject_scheme":"Other"},{"subitem_subject":"HOPE","subitem_subject_scheme":"Other"},{"subitem_subject":"H-2ロケット打上げ型有翼宇宙往還機","subitem_subject_scheme":"Other"},{"subitem_subject":"大気圏再突入","subitem_subject_scheme":"Other"},{"subitem_subject":"超音速風洞","subitem_subject_scheme":"Other"},{"subitem_subject":"鈍頭物体","subitem_subject_scheme":"Other"},{"subitem_subject":"鈍頭模型","subitem_subject_scheme":"Other"},{"subitem_subject":"風見安定","subitem_subject_scheme":"Other"},{"subitem_subject":"層流遷移バブル","subitem_subject_scheme":"Other"},{"subitem_subject":"層流剥離バブル","subitem_subject_scheme":"Other"},{"subitem_subject":"抗力係数","subitem_subject_scheme":"Other"},{"subitem_subject":"揚力係数","subitem_subject_scheme":"Other"},{"subitem_subject":"縦揺れモーメント","subitem_subject_scheme":"Other"},{"subitem_subject":"風洞実験","subitem_subject_scheme":"Other"},{"subitem_subject":"OREX","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"orbital reentry experiment vehicle","subitem_subject_language":"en","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":"atmosphere reentry","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"supersonic wind tunnel","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"blunt body","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"blunted model","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"vane stable","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"laminar transition bubble","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"laminar separation bubble","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"drag coefficient","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"lift coefficient","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"pitching movement","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"wind tunnel test","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":"超音速における軌道再突入実験機模型の空力特性","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"超音速における軌道再突入実験機模型の空力特性"}]},"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":"39806","relation_version_is_last":true,"title":["超音速における軌道再突入実験機模型の空力特性"],"weko_creator_id":"1","weko_shared_id":1},"updated":"2023-06-20T19:19:00.214817+00:00"}