WEKO3
アイテム
{"_buckets": {"deposit": "4cf57c16-8b95-40ab-8941-623ad7af570c"}, "_deposit": {"created_by": 1, "id": "5743", "owners": [1], "pid": {"revision_id": 0, "type": "depid", "value": "5743"}, "status": "published"}, "_oai": {"id": "oai:jaxa.repo.nii.ac.jp:00005743", "sets": ["1005", "1891"]}, "author_link": ["476854", "476857", "476852", "476853", "476859", "476856", "476858", "476855"], "item_5_biblio_info_10": {"attribute_name": "書誌情報", "attribute_value_mlt": [{"bibliographicIssueDates": {"bibliographicIssueDate": "2007-03-30", "bibliographicIssueDateType": "Issued"}, "bibliographicPageEnd": "83", "bibliographicPageStart": "78", "bibliographicVolumeNumber": "JAXA-SP-06-029E", "bibliographic_titles": [{"bibliographic_title": "宇宙航空研究開発機構特別資料"}, {"bibliographic_title": "JAXA Special Publication: Proceedings of International Workshops on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport (SST-CFD Workshop)", "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": "SST-CFD Workshop. International CFD Workshops for Super-sonic Transport Design 航空宇宙技術研究所 19980316-19980317 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": "SST-CFD Workshop. International CFD Workshops for Super-sonic Transport Design National Aerospace Laboratory 19980316-19980317 Tokyo Japan", "subitem_description_type": "Other"}]}, "item_5_description_17": {"attribute_name": "抄録(英)", "attribute_value_mlt": [{"subitem_description": "Aerodynamic shape of a wing for NAL\u0027s SST (SuperSonic Transport) has been designed by a supersonic inverse design method. This method handles SST\u0027s wing-fuselage configurations and provides wing section\u0027s geometry at every span. The design system consists of a new inverse problem solver and a Navier-Stokes simulation. The design procedure is iterative; the baseline shape is Successively modified as the process of the inverse problem solver and Navier-Stokes simulation is iterated until the pressure distribution given by the designed wing can be regarded to converge to the target one. The design target is a NLF (Natural Laminar Flow) wing for the wing-fuselage combination at the speed of M(sub infinity) = 2.0. Several design constraints have been intended to be satisfied. By means of the method, a better wing shape which has much more desirable characteristics has been designed than that by the traditional linear theory.", "subitem_description_type": "Other"}]}, "item_5_description_32": {"attribute_name": "資料番号", "attribute_value_mlt": [{"subitem_description": "資料番号: AA0063609012", "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: JAXA-SP-06-029E", "subitem_description_type": "Other"}]}, "item_5_publisher_8": {"attribute_name": "出版者", "attribute_value_mlt": [{"subitem_publisher": "宇宙航空研究開発機構"}]}, "item_5_publisher_9": {"attribute_name": "出版者(英)", "attribute_value_mlt": [{"subitem_publisher": "Japan Aerospace Exploration Agency (JAXA)"}]}, "item_5_source_id_21": {"attribute_name": "ISSN", "attribute_value_mlt": [{"subitem_source_identifier": "1349-113X", "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": "AA11984031", "subitem_source_identifier_type": "NCID"}]}, "item_5_text_20": {"attribute_name": "その他キーワード", "attribute_value_mlt": [{"subitem_text_value": "航空機の設計、試験及び性能"}, {"subitem_text_value": "数値解析"}, {"subitem_text_value": "航空力学"}]}, "item_5_text_35": {"attribute_name": "JAXAカテゴリ", "attribute_value_mlt": [{"subitem_text_value": "JAXAカテゴリ: 特別資料"}]}, "item_5_text_40": {"attribute_name": "jaxa出版物種類", "attribute_value_mlt": [{"subitem_text_value": "jaxa出版物種類: SP"}]}, "item_5_text_43": {"attribute_name": "DSpaceコレクション番号", "attribute_value_mlt": [{"subitem_text_value": "DSpaceコレクション番号: 7"}]}, "item_5_text_6": {"attribute_name": "著者所属", "attribute_value_mlt": [{"subitem_text_value": "富士通"}, {"subitem_text_value": "航空宇宙技術研究所"}, {"subitem_text_value": "東北大学"}, {"subitem_text_value": "東北大学"}]}, "item_5_text_7": {"attribute_name": "著者所属(英)", "attribute_value_mlt": [{"subitem_text_language": "en", "subitem_text_value": "Fujitsu Ltd."}, {"subitem_text_language": "en", "subitem_text_value": "National Aerospace Laboratory"}, {"subitem_text_language": "en", "subitem_text_value": "Tohoku University"}, {"subitem_text_language": "en", "subitem_text_value": "Tohoku University"}]}, "item_creator": {"attribute_name": "著者", "attribute_type": "creator", "attribute_value_mlt": [{"creatorNames": [{"creatorName": "松島, 紀佐"}], "nameIdentifiers": [{"nameIdentifier": "476852", "nameIdentifierScheme": "WEKO"}]}, {"creatorNames": [{"creatorName": "岩宮, 敏幸"}], "nameIdentifiers": [{"nameIdentifier": "476853", "nameIdentifierScheme": "WEKO"}]}, {"creatorNames": [{"creatorName": "Jeong, Shinkyu"}], "nameIdentifiers": [{"nameIdentifier": "476854", "nameIdentifierScheme": "WEKO"}]}, {"creatorNames": [{"creatorName": "大林, 茂"}], "nameIdentifiers": [{"nameIdentifier": "476855", "nameIdentifierScheme": "WEKO"}]}, {"creatorNames": [{"creatorName": "Matsushima, Kisa", "creatorNameLang": "en"}], "nameIdentifiers": [{"nameIdentifier": "476856", "nameIdentifierScheme": "WEKO"}]}, {"creatorNames": [{"creatorName": "Iwamiya, Toshiyuki", "creatorNameLang": "en"}], "nameIdentifiers": [{"nameIdentifier": "476857", "nameIdentifierScheme": "WEKO"}]}, {"creatorNames": [{"creatorName": "Jeong, Shinkyu", "creatorNameLang": "en"}], "nameIdentifiers": [{"nameIdentifier": "476858", "nameIdentifierScheme": "WEKO"}]}, {"creatorNames": [{"creatorName": "Obayashi, Shigeru", "creatorNameLang": "en"}], "nameIdentifiers": [{"nameIdentifier": "476859", "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": "2020-02-10"}], "displaytype": "detail", "download_preview_message": "", "file_order": 0, "filename": "63609012.pdf", "filesize": [{"value": "2.7 MB"}], "format": "application/pdf", "future_date_message": "", "is_thumbnail": false, "licensetype": "license_free", "mimetype": "application/pdf", "size": 2700000.0, "url": {"label": "63609012.pdf", "url": "https://jaxa.repo.nii.ac.jp/record/5743/files/63609012.pdf"}, "version_id": "3813e41c-d62f-4d34-b2f6-7b8356832c7b"}]}, "item_keyword": {"attribute_name": "キーワード", "attribute_value_mlt": [{"subitem_subject": "超音速機", "subitem_subject_scheme": "Other"}, {"subitem_subject": "航空機設計", "subitem_subject_scheme": "Other"}, {"subitem_subject": "民間航空", "subitem_subject_scheme": "Other"}, {"subitem_subject": "計算流体力学", "subitem_subject_scheme": "Other"}, {"subitem_subject": "胴翼結合", "subitem_subject_scheme": "Other"}, {"subitem_subject": "反復解法", "subitem_subject_scheme": "Other"}, {"subitem_subject": "圧力分布", "subitem_subject_scheme": "Other"}, {"subitem_subject": "設計最適化", "subitem_subject_scheme": "Other"}, {"subitem_subject": "層流境界層", "subitem_subject_scheme": "Other"}, {"subitem_subject": "マッハ数", "subitem_subject_scheme": "Other"}, {"subitem_subject": "supersonic aircraft", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "aircraft design", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "civil aviation", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "computational fluid dynamics", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "wing-fuselage combination", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "iterative solution", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "pressure distribution", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "design optimization", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "laminar boundary layer", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}, {"subitem_subject": "Mach number", "subitem_subject_language": "en", "subitem_subject_scheme": "Other"}]}, "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": "conference paper", "resourceuri": "http://purl.org/coar/resource_type/c_5794"}]}, "item_title": "Aerodynamic wing design for NAL\u0027s SST using iterative inverse approach", "item_titles": {"attribute_name": "タイトル", "attribute_value_mlt": [{"subitem_title": "Aerodynamic wing design for NAL\u0027s SST using iterative inverse approach", "subitem_title_language": "en"}]}, "item_type_id": "5", "owner": "1", "path": ["1005", "1891"], "permalink_uri": "https://jaxa.repo.nii.ac.jp/records/5743", "pubdate": {"attribute_name": "公開日", "attribute_value": "2015-03-26"}, "publish_date": "2015-03-26", "publish_status": "0", "recid": "5743", "relation": {}, "relation_version_is_last": true, "title": ["Aerodynamic wing design for NAL\u0027s SST using iterative inverse approach"], "weko_shared_id": -1}
Aerodynamic wing design for NAL's SST using iterative inverse approach
https://jaxa.repo.nii.ac.jp/records/5743
https://jaxa.repo.nii.ac.jp/records/57432860b0c0-dcbf-4347-be13-db01093aaf6c
名前 / ファイル | ライセンス | アクション |
---|---|---|
63609012.pdf (2.7 MB)
|
|
Item type | 会議発表論文 / Conference Paper(1) | |||||
---|---|---|---|---|---|---|
公開日 | 2015-03-26 | |||||
タイトル | ||||||
言語 | en | |||||
タイトル | Aerodynamic wing design for NAL's SST using iterative inverse approach | |||||
言語 | ||||||
言語 | eng | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 超音速機 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 航空機設計 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 民間航空 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 計算流体力学 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 胴翼結合 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 反復解法 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 圧力分布 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 設計最適化 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 層流境界層 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | マッハ数 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | supersonic aircraft | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | aircraft design | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | civil aviation | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | computational fluid dynamics | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | wing-fuselage combination | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | iterative solution | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | pressure distribution | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | design optimization | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | laminar boundary layer | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Mach number | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_5794 | |||||
資源タイプ | conference paper | |||||
著者 |
松島, 紀佐
× 松島, 紀佐× 岩宮, 敏幸× Jeong, Shinkyu× 大林, 茂× Matsushima, Kisa× Iwamiya, Toshiyuki× Jeong, Shinkyu× Obayashi, Shigeru |
|||||
著者所属 | ||||||
富士通 | ||||||
著者所属 | ||||||
航空宇宙技術研究所 | ||||||
著者所属 | ||||||
東北大学 | ||||||
著者所属 | ||||||
東北大学 | ||||||
著者所属(英) | ||||||
en | ||||||
Fujitsu Ltd. | ||||||
著者所属(英) | ||||||
en | ||||||
National Aerospace Laboratory | ||||||
著者所属(英) | ||||||
en | ||||||
Tohoku University | ||||||
著者所属(英) | ||||||
en | ||||||
Tohoku University | ||||||
出版者 | ||||||
出版者 | 宇宙航空研究開発機構 | |||||
出版者(英) | ||||||
出版者 | Japan Aerospace Exploration Agency (JAXA) | |||||
書誌情報 |
宇宙航空研究開発機構特別資料 en : JAXA Special Publication: Proceedings of International Workshops on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport (SST-CFD Workshop) 巻 JAXA-SP-06-029E, p. 78-83, 発行日 2007-03-30 |
|||||
会議概要(会議名, 開催地, 会期, 主催者等) | ||||||
内容記述タイプ | Other | |||||
内容記述 | SST-CFD Workshop. International CFD Workshops for Super-sonic Transport Design 航空宇宙技術研究所 19980316-19980317 東京 日本 | |||||
会議概要(会議名, 開催地, 会期, 主催者等)(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | SST-CFD Workshop. International CFD Workshops for Super-sonic Transport Design National Aerospace Laboratory 19980316-19980317 Tokyo Japan | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Aerodynamic shape of a wing for NAL's SST (SuperSonic Transport) has been designed by a supersonic inverse design method. This method handles SST's wing-fuselage configurations and provides wing section's geometry at every span. The design system consists of a new inverse problem solver and a Navier-Stokes simulation. The design procedure is iterative; the baseline shape is Successively modified as the process of the inverse problem solver and Navier-Stokes simulation is iterated until the pressure distribution given by the designed wing can be regarded to converge to the target one. The design target is a NLF (Natural Laminar Flow) wing for the wing-fuselage combination at the speed of M(sub infinity) = 2.0. Several design constraints have been intended to be satisfied. By means of the method, a better wing shape which has much more desirable characteristics has been designed than that by the traditional linear theory. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 1349-113X | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AA11984031 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0063609012 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | レポート番号: JAXA-SP-06-029E |