{"created":"2023-06-20T14:36:16.537023+00:00","id":2588,"links":{},"metadata":{"_buckets":{"deposit":"793b20be-5ebd-4748-a65e-43ea11a0e70a"},"_deposit":{"created_by":1,"id":"2588","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"2588"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00002588","sets":["1887:1893","9:1090:1241:1242"]},"author_link":["7540","7539"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Aerodynamic design of 3.5th configuration air intake for silent supersonic technology demonstrator S3TD"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2009-03-31","bibliographicIssueDateType":"Issued"},"bibliographicVolumeNumber":"JAXA-RM-08-019","bibliographic_titles":[{"bibliographic_title":"宇宙航空研究開発機構研究開発資料"},{"bibliographic_title":"JAXA Research and Development Memorandum","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"宇宙航空研究開発機構で基本設計検討が進められている静粛超音速研究機のインテークについて基本設計相当の設計作業を行った．本研究では基本設計ベースライン形状を設計の開始点とし，静粛超音速研究機の飛行ミッションが成立するために要求されるインテーク性能を満足するよう，CFD解析と風洞試験により設計検討が進められている．基本設計検討では，基本設計ベースライン形状の問題点である低速域の流量特性を改善することと，流れ場の改善と外部抵抗低減を目的とした抽気流量の設定を行うことで，空力形状の改善と改善された形状の空力性能を取得することが目的である．低速域の流量特性を改善するために，カウル平面形と断面形状の検討を行い，想定される飛行エンベロープ全体でエンジンの運用に十分な流量を供給することができるカウル形状が設計されたが，その結果，超音速飛行時の外部抵抗は増加することが分かった．抵抗増加を抑えるためには捕獲面積を小さくすることが有効であるが，捕獲面積を小さくする際に必要となる補助ドアについて検討を行い，その有効性を明らかにした．インテークの総圧回復性能，ディストーション性能および外部抵抗に及ぼす抽気の影響を調べることで，抽気特性を明確にし，抽気位置と流量を設定した．また，逆流防止機能の必要性を明確にし，その機能の作動点を設定した．以上の検討を基に静粛超音速研究機用インテークの第3.5次形状が設計され，CFDによる性能推算を行った結果，総圧回復性能は抽気を適用することで向上し，設計点においてほぼMIL規格の性能が達成されることが分かった．空間ディストーション性能については今後風洞試験により，その特性を明らかにする必要がある．外部抵抗については，カウル形状および抽気の効果を明らかにし，抵抗増加を抑えつつ，低速時の流量特性が改善されていることを確認した．","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"The air-intake for the silent supersonic technology demonstrator, S3TD, is being designed in Japan Aerospace Exploration Agency. The aerodynamic design based on the base line of preliminary design configuration was improved by means of CFD analysis and wind tunnel tests. Improving the flow characteristics of the base line configuration air-intake in low speed region is one of the main objectives in this study. In order to do that, both the plane shape and the thickness of cowl lip were examined experimentally and numerically. The characteristic of flow was improved by the latest design shape of the cowl, whereas the aerodynamic drag was found to be impaired. Application of the auxiliary inlet was also examined to improve the flow characteristic of air-intake in low speed region without impairing the aerodynamic drag. Bleed system, which is another main object of this study, was also examined experimentally and numerically. Dimensions of porous bleed wall and quantity of bleed air were designed to improve the pressure recovery, as well as to reduce the external drag of air-intake.","subitem_description_type":"Other"}]},"item_3_description_18":{"attribute_name":"内容記述","attribute_value_mlt":[{"subitem_description":"形態: カラー図版あり","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0064397000","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: JAXA-RM-08-019","subitem_description_type":"Other"}]},"item_3_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"宇宙航空研究開発機構"}]},"item_3_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"Japan Aerospace Exploration Agency (JAXA)"}]},"item_3_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"1349-1121","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":"AA11983593","subitem_source_identifier_type":"NCID"}]},"item_3_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"宇宙航空研究開発機構航空プログラムグループ超音速機チーム"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Supersonic Transport Team，Aviation Program Group, Japan Aerospace Exploration Agency (JAXA)"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"渡辺, 安"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Watanabe, Yasushi","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":"2020-01-15"}],"displaytype":"detail","filename":"64397000.pdf","filesize":[{"value":"8.2 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"64397000.pdf","url":"https://jaxa.repo.nii.ac.jp/record/2588/files/64397000.pdf"},"version_id":"0a97f97f-329f-49c5-a1fc-dd003ab6a4e3"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"Silent Super Sonic Technology Demonstrator, air-intake, aerodynamic design, wind tunnel test, CFD","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":"静粛超音速研究機(S3TD)第3.5次形状インテークの空力設計","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"静粛超音速研究機(S3TD)第3.5次形状インテークの空力設計"}]},"item_type_id":"3","owner":"1","path":["1242","1893"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"2588","relation_version_is_last":true,"title":["静粛超音速研究機(S3TD)第3.5次形状インテークの空力設計"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T09:19:31.878344+00:00"}