{"created":"2023-06-20T15:08:05.006734+00:00","id":37471,"links":{},"metadata":{"_buckets":{"deposit":"f5b103fa-d21b-47d9-81ea-62dbca3f5f3e"},"_deposit":{"created_by":1,"id":"37471","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"37471"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00037471","sets":["1887:1891","1896:1898:1913:1915"]},"author_link":["480962","480965","480961","480964","480957","480966","480958","480963","480959","480960"],"item_5_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Flow simulation of NAL experimental supersonic airplane/booster separation using overset unstructured grids"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1999-12","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"250","bibliographicPageStart":"245","bibliographicVolumeNumber":"44","bibliographic_titles":[{"bibliographic_title":"航空宇宙技術研究所特別資料"},{"bibliographic_title":"Special Publication of National Aerospace Laboratory","bibliographic_titleLang":"en"}]}]},"item_5_description_14":{"attribute_name":"会議概要（会議名, 開催地, 会期, 主催者等）","attribute_value_mlt":[{"subitem_description":"航空宇宙技術研究所 16-18 Jun. 1999 東京 日本","subitem_description_type":"Other"}]},"item_5_description_15":{"attribute_name":"会議概要（会議名, 開催地, 会期, 主催者等）（英）","attribute_value_mlt":[{"subitem_description":"National Aerospace Laboratory 16-18 Jun. 1999 Tokyo Japan","subitem_description_type":"Other"}]},"item_5_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"非構造格子オーバーセット法のための格子間境界を局所化する効率的でロバストなアルゴリズムを提案した。基本パラメータとして物体壁面からの距離を用いて格子間境界定義を簡単にし、自動化を実現した。隣から隣へジャンプして探索するアルゴリズムを効率的に用いた。Delaunyの3角法による副産物として生成される補助格子を使うことによって探索のロバスト性および効率を改善した。本法の基本的な手順は多要素翼問題に対して記述されている。ONERA-M6翼によりオーバーセット法の解の精度と収束性への影響を試験した。非構造格子オーバーセット法を用いて超音速実験機とロケットブースタの分離シミュレーションを行った。シミュレーションでは航空機とロケットブースタをそれぞれ別にカバーする2つの非構造格子を用いる。ロケットブースタの周りの格子は時間とともに航空機周りの静止格子の中を移動する。計算結果はこの2つの物体間の衝撃波パターンを鮮明にシミュレートした。実験結果との比較から航空機とブースタの分離過程間の揚力係数とピッチングモーメント係数についてよい一致を示すことが分かった。","subitem_description_type":"Abstract"}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"In this paper, an efficient and robust algorithm to localize the intergrid boundaries for the overset unstructured grid method is proposed. The simplicity and automation in the intergrid-boundary definition are realized using the wall distance and a basic parameter. The neighbor-to-neighbor jump search algorithm is efficiently utilized in the method. The robustness and efficiency of the search are improved by a use of subsidiary grids that are generated as a byproduct of the Delaunay triangulation method. The basic procedure of the present method is described for a multi-element airfoil problem. The effect of the overset method to the solution accuracy and the convergence are tested by the ONERA M6 wing. The overset unstructured grid method is applied to a flow simulation about an experimental supersonic airplane separation from a rocket booster. Two unstructured grids, each of which covers the airplane and the rocket booster respectively, are used for the simulation. The grid around the rocket booster moves with time in the stationary grid about the airplane. The computed result clearly simulates the shock wave patterns between two bodies. Comparisons with the experimental results show good agreements in the lift and pitching moment coefficients of the airplane and booster during the separation process.","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0001961038","subitem_description_type":"Other"}]},"item_5_description_33":{"attribute_name":"レポート番号","attribute_value_mlt":[{"subitem_description":"レポート番号: NAL SP-44","subitem_description_type":"Other"}]},"item_5_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"航空宇宙技術研究所"}]},"item_5_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"National Aerospace Laboratory (NAL)"}]},"item_5_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"0289-260X","subitem_source_identifier_type":"ISSN"}]},"item_5_source_id_24":{"attribute_name":"書誌レコードID","attribute_value_mlt":[{"subitem_source_identifier":"AN10097345","subitem_source_identifier_type":"NCID"}]},"item_5_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"東北大学"},{"subitem_text_value":"東北大学"},{"subitem_text_value":"東北大学"},{"subitem_text_value":"三菱重工業"},{"subitem_text_value":"航空宇宙技術研究所"}]},"item_5_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Tohoku University"},{"subitem_text_language":"en","subitem_text_value":"Tohoku University"},{"subitem_text_language":"en","subitem_text_value":"Tohoku University"},{"subitem_text_language":"en","subitem_text_value":"Mitsubishi Heavy Industries Ltd"},{"subitem_text_language":"en","subitem_text_value":"National Aerospace Laboratory"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"富樫, 史弥"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"中橋, 和博"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"伊藤, 靖"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"森野, 裕行"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"岩宮, 敏幸"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Togashi, Fumiya","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Nakahashi, Kazuhiro","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Ito, Yasushi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Morino, Hiroyuki","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Iwamiya, Toshiyuki","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":"2020-02-10"}],"displaytype":"detail","filename":"nalsp0044038.pdf","filesize":[{"value":"1.3 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"nalsp0044038.pdf","url":"https://jaxa.repo.nii.ac.jp/record/37471/files/nalsp0044038.pdf"},"version_id":"88cff5b2-7505-469d-9332-e29db66f6a1d"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"多要素翼","subitem_subject_scheme":"Other"},{"subitem_subject":"超音速実験機","subitem_subject_scheme":"Other"},{"subitem_subject":"非構造格子","subitem_subject_scheme":"Other"},{"subitem_subject":"オーバーセット格子","subitem_subject_scheme":"Other"},{"subitem_subject":"収束履歴","subitem_subject_scheme":"Other"},{"subitem_subject":"ONERA M6翼","subitem_subject_scheme":"Other"},{"subitem_subject":"ロケットブースタ分離","subitem_subject_scheme":"Other"},{"subitem_subject":"シミュレーション","subitem_subject_scheme":"Other"},{"subitem_subject":"衝撃波","subitem_subject_scheme":"Other"},{"subitem_subject":"キメラ領域","subitem_subject_scheme":"Other"},{"subitem_subject":"揚力係数","subitem_subject_scheme":"Other"},{"subitem_subject":"ピッチングモーメント係数","subitem_subject_scheme":"Other"},{"subitem_subject":"multi element airfoil","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"experimental supersonic airplane","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"unstructured grid method","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"overset grid","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"convergence history","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"ONERA M six wing","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"rocket booster separation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"simulation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"shock wave","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"chimera hole","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"lift coefficient","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"pitching moment coefficient","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":"conference paper","resourceuri":"http://purl.org/coar/resource_type/c_5794"}]},"item_title":"非構造オーバーセット格子による超音速実験機・ブースター分離シミュレーション","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"非構造オーバーセット格子による超音速実験機・ブースター分離シミュレーション"}]},"item_type_id":"5","owner":"1","path":["1891","1915"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"37471","relation_version_is_last":true,"title":["非構造オーバーセット格子による超音速実験機・ブースター分離シミュレーション"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-20T21:18:07.870678+00:00"}