{"created":"2023-06-20T15:10:18.569086+00:00","id":39894,"links":{},"metadata":{"_buckets":{"deposit":"42fe0eb7-4efb-4d29-b386-39870bc5a0fc"},"_deposit":{"created_by":1,"id":"39894","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"39894"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00039894","sets":["1887:1893","1896:1898:1913:1916"]},"author_link":["445518","445517","445505","445508","445509","445515","445520","445507","445510","445504","445511","445519","445506","445516","445514","445512","445513","445521"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Wind tunnel tests of HYFLEX vehicles in the NAL shock tunnel"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1997-01","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"16","bibliographicPageStart":"1","bibliographicVolumeNumber":"708","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所資料"},{"bibliographic_title":"Technical Memorandum 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)の研究開発の一環として、1996年2月に極超音速飛行実験(HYFLEX)が行われた。HYFLEX計画の初期において、飛行実験および実験機についてケーススタディ的に行われた研究の一環として、航技研中型衝撃風洞(M10.8)で実施した衝撃風洞試験結果をまとめたものである。風洞試験は、2段式J-1ロケットの先端に露出して搭載されることを想定したデルタ翼をもつ有翼形状、および同ロケットの衛星フェアリング内に搭載されることを想定したリフティングボディ形状について、複数の形態に対して実施した。本試験の目的は、基本形状などの空力特性を調べる他、形状変化の効果、ニュートニアン理論による空力特性推算の精度、および粘性干渉効果についての知見を得ることである。この試験で得られた空力特性に関する知見、およびニュートニアン理論により、この種の機体について空力特性の推算が可能であるという結論に基づき、HYFLEXの開発のベースラインとなる形状設計が行われた。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"A Hypersonic Flight Experiment (HYFLEX), which is one of the flight experiment series prior to the development of HOPE-X (H-2 Orbiting Plane-X), was conducted on February 12, 1996 as a joint project between NAL and NASDA (National Space Development Agency of Japan). As a part of the conceptual study of HYFLEX by NAL, six-component force tests of two different vehicle types were performed at Mach 10.8 using NAL middle scale shock tunnel. One model used delta wings (HRV02) and the other had the so-called lifting body configuration (HRV03), both of which were assumed to be launched by a two-stage version of the J-1 launcher of NASDA. The results of the present test were used in the trade-off study of the vehicle's configuration. The results were also compared with numerical prediction using Newtonian flow assumption and Prandtl-Meyer expansion in order to estimate the accuracy of such a method; this method was employed in the determination of the base-line configuration for preliminary design of HYFLEX.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0000872000","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 TM-708","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":"0452-2982","subitem_source_identifier_type":"ISSN"}]},"item_3_source_id_24":{"attribute_name":"書誌レコードID","attribute_value_mlt":[{"subitem_source_identifier":"AN00314334","subitem_source_identifier_type":"NCID"}]},"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 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 新型航空機研究グループ"},{"subitem_text_value":"航空宇宙技術研究所 数理解析部"},{"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 原動機部"},{"subitem_text_value":"東北大学 工学部"},{"subitem_text_value":"航空宇宙技術研究所 機体部"}]},"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 Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Advanced Aircraft Research Group"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Computational Sciences Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aerodynamics Division"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Aeroengine Division"},{"subitem_text_language":"en","subitem_text_value":"Tohoku University Faculty of Engineering"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory Airframe Division"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"白水, 正男"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"渡辺, 重哉"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"山崎, 喬"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"伊藤, 健"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"和田, 安弘"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"永井, 伸治"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"村上, 哲"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"溝端, 一秀"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"少路, 宏和"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Shirouzu, Masao","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Watanabe, Shigeya","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Yamazaki, Takashi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Ito, Takeshi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Wada, Yasuhiro","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Nagai, Shinji","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Murakami, Akira","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Mizobata, Kazuhide","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Shoji, Hirokazu","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":"naltm0000708.pdf","filesize":[{"value":"401.1 kB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltm0000708.pdf","url":"https://jaxa.repo.nii.ac.jp/record/39894/files/naltm0000708.pdf"},"version_id":"bb47888c-4e48-46e2-bd31-e4c32bd5acab"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"HYFLEX","subitem_subject_scheme":"Other"},{"subitem_subject":"極超音速飛行実験","subitem_subject_scheme":"Other"},{"subitem_subject":"衝撃風洞","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回収機","subitem_subject_scheme":"Other"},{"subitem_subject":"J-1ロケット","subitem_subject_scheme":"Other"},{"subitem_subject":"デルタ翼","subitem_subject_scheme":"Other"},{"subitem_subject":"有翼形状","subitem_subject_scheme":"Other"},{"subitem_subject":"リフティングボディ形状","subitem_subject_scheme":"Other"},{"subitem_subject":"空力特性","subitem_subject_scheme":"Other"},{"subitem_subject":"粘性干渉","subitem_subject_scheme":"Other"},{"subitem_subject":"プラントルマイヤー膨張流","subitem_subject_scheme":"Other"},{"subitem_subject":"ニュートン理論","subitem_subject_scheme":"Other"},{"subitem_subject":"6分力試験","subitem_subject_scheme":"Other"},{"subitem_subject":"HYFLEX","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"hypersonic flight experiment","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"shock wind tunnel","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":"J 1 rocket","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"delta wing","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"winged configuration","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"lifting body configuration","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"aerodynamic characteristics","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"viscosity interference","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Prandtl Meyer expansion flow","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Newtonian theory","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"six component force 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":"極超音速飛行実験機の衝撃風洞試験","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"極超音速飛行実験機の衝撃風洞試験"}]},"item_type_id":"3","owner":"1","path":["1893","1916"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"39894","relation_version_is_last":true,"title":["極超音速飛行実験機の衝撃風洞試験"],"weko_creator_id":"1","weko_shared_id":1},"updated":"2023-06-20T19:18:30.182071+00:00"}