{"created":"2023-06-20T15:15:16.766513+00:00","id":45352,"links":{},"metadata":{"_buckets":{"deposit":"ebb7c62f-1621-4cb8-9c18-243f3888bc13"},"_deposit":{"created_by":1,"id":"45352","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"45352"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00045352","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["474307","474308","474309","474310"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Numerical Simulation of Hypersonic Viscous Flow for the Design of H-II Orbiting Plane(HOPE)II"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1991-01","bibliographicIssueDateType":"Issued"},"bibliographicPageStart":"76","bibliographicVolumeNumber":"1093","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所報告"},{"bibliographic_title":"Technical Report of National Aerospace Laboratory TR-1093","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"航空宇宙技術研究所と宇宙開発事業団との共同研究「H-IIロケット打上げ型有翼宇宙往還機(HOPE)の研究」の一環として,平成元年度に行った極超音速領域の空力数値解析に関する成果を報告する。形状はHOPE63基本形状及び主翼後退角を大きくしたHOPE63W-2形状について,空力加熱分布,レイノルズ数効果,マッハ数効果,および設計上不可欠なコントロールの問題(空力舵面,ガスジェット)について詳細に調べた。計算結果は極超音速風洞における実験結果と比較し,空力加熱分布について定量的にすぐれた一致が得られた。本研究の目的は1)HOPEの空力加熱特性を定量的に把握し,2)実験値との比較を通して本数値シミュレーションの信頼性,適用性を検討し,3)あわせて数値解析をHOPEの耐熱構造設計およびコントロールの問題を含む空力形状設計のための主要な手段として役立てることにある。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"An unmanned winged vehicle for space transportation, the H-II Orbiting Plane(HOPE), is being studied by the National Space Development Agency of JAPAN(NASDA). Hypersonic computational fluid dynamic(CFD) analyses were performed on the NASDA proposed HOPE63 model, with the effects of Reynolds number, Mach number, angles of attack, and yaw angles. In order to use CFD for more practical design purposes, analyses of control surfaces and the gas jet are also discussed. The present study's objectives were to :1)Demonstrate the numerical code's validity for aerothermodynamic heating, 2)Investigate the applicability of CFD to control problem, and 3)Utilize CFD as the main design tool of the HOPE configuration, i.g., utilize it as a numerical wind tunnel. Numerical simulations were conducted using the flux split upwind Navier-Stokes code, and results showed excellent agreement with heat transfer distribution experiments, thereby demonstrating the present code′s validity.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: NALTR1093000","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-1093","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":"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":"Aerodynamics Division, National Aerospace Laboratory(NAL)"},{"subitem_text_language":"en","subitem_text_value":"National Space Development Agency of Japan(NASDA)"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"山本, 行光"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"秋元, 敏男"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"YAMAMOTO, Yukimitsu","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":"2020-01-29"}],"displaytype":"detail","filename":"naltr01093.pdf","filesize":[{"value":"9.8 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr01093.pdf","url":"https://jaxa.repo.nii.ac.jp/record/45352/files/naltr01093.pdf"},"version_id":"f3852573-324d-446b-953b-1d32d02a5318"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"Hypersonic Viscuss Flow;  Re-Entry Vehicle Aerodynamics;  Computational Fluid Dynamics;  Aerothermodynamics Heating","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の極超音速空力数値シミュレーションII","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"HOPEの極超音速空力数値シミュレーションII"}]},"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":"45352","relation_version_is_last":true,"title":["HOPEの極超音速空力数値シミュレーションII"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:40:56.390237+00:00"}