{"created":"2023-06-20T15:15:11.143573+00:00","id":45235,"links":{},"metadata":{"_buckets":{"deposit":"b0e29101-8ef3-4eef-b411-22f81a60c691"},"_deposit":{"created_by":1,"id":"45235","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"45235"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00045235","sets":["1887:1893","1896:1898:1913:1917"]},"author_link":["473642","473641","473640"],"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1988-05","bibliographicIssueDateType":"Issued"},"bibliographicPageStart":"21","bibliographicVolumeNumber":"976T","bibliographic_titles":[{},{"bibliographic_title":"Technical Report of National Aerospace Laboratory TR-976T","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"Thomas-Van Leerらによる流束分離風上TVD差分法をスペース・プレーンまわりの極超音速流の解析に適用した。基礎方程式は有限体積表示の薄層近似ナビエ・ストークス方程式で,解法としてImplicit Approximate Factorization法を用いた。数値計算はマッハ数7.0,レイノルズ数1.3×107で迎角は5°間隔で0°から30°までのCaseについて行った。計算結果は当所の極超音速風洞で行われた実験結果と比較され,スペース・プレーンの設計において重要な空力及び空力加熱の評価に,十分信頼性にたえるデータを提供することが判明した。本解析においては,さらにYee-HartenらによるTVD差分法を一部修正し,マッハ数10.0,迎角0°のCaseに適用し,前者のスキームによる計算結果との比較を行った。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"Thomas ＆ Van Leer’s flux-split upwind TVD scheme has been applied to the hypersonic flow around a space proposed by National Aerospace Laboratory (NAL). In this paper, thin-layer Navier-Stokes equations in finite volume formulation are solved by using an implicit approximately factored ADI algorithm. Numerical computations are performed for a Mach number of 7.0 and Reynolds number of 1.3 ×10(exp 7) at angles of attack up to 30 degrees. Numerical results are compared with experimental data obtained from the hypersonic wind tunnel tests at NAL. Through these comparisons, it is demonstrated that the present TVD Navier-Stokes code excellent capabilities for evaluating total aerodynamic performance and investigating severe aerodynamic heating, which are of great significance in the design of a space plane configuration. In the present analysis, a modified Yee-Harten’s TVD scheme is also developed and applied. Numerical calculations have been carried out by using these two schemes for M∞=10.0 at α=0 deg and almost the same pressure contours were obtained.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: NALTR0976000","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-976T","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"}]},"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":"Total Systems Inc."}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"山本, 行光"}],"nameIdentifiers":[{"nameIdentifier":"473640","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"YAMAMOTO, Yukimitsu","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"473641","nameIdentifierScheme":"WEKO"}]},{"creatorNames":[{"creatorName":"KUBO, Shin","creatorNameLang":"en"}],"nameIdentifiers":[{"nameIdentifier":"473642","nameIdentifierScheme":"WEKO"}]}]},"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":"naltr0976t.pdf","filesize":[{"value":"1.7 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"naltr0976t.pdf","url":"https://jaxa.repo.nii.ac.jp/record/45235/files/naltr0976t.pdf"},"version_id":"88ddc6a1-a5e0-41e0-b76e-7b44f86db82a"}]},"item_language":{"attribute_name":"言語","attribute_value_mlt":[{"subitem_language":"eng"}]},"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":"Numerical Simulation of Hypersonic Flow around a Space Plane I Basic Development","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Numerical Simulation of Hypersonic Flow around a Space Plane I Basic Development","subitem_title_language":"en"}]},"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":"45235","relation_version_is_last":true,"title":["Numerical Simulation of Hypersonic Flow around a Space Plane I Basic Development"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:42:54.616692+00:00"}