{"created":"2023-06-20T14:36:15.599292+00:00","id":2570,"links":{},"metadata":{"_buckets":{"deposit":"18288646-0b48-48f4-9a44-7b155606aa3d"},"_deposit":{"created_by":1,"id":"2570","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"2570"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00002570","sets":["1887:1893","9:1090:1210:1222"]},"author_link":["7326","7328","7323","7325","7327","7324"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Supersonic Wind Tunnel Test for 3.5th Configuration Air Intake of Silent SuperSonic Technology Demonstrator S3TD"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2010-07-15","bibliographicIssueDateType":"Issued"},"bibliographicVolumeNumber":"JAXA-RM-10-008","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は静粛超音速機技術の研究開発の一環として，静粛超音速研究機の基本設計相当の作業が実施された．その設計作業の一環として第3.5 次形状インテークの設計を行った．本研究では第3.5次形状インテークを対象に超音速域の空力性能データベースを作成することを目的として超音速風洞試験を実施した．本インテークは胴体上面に配置されているため，超音速域では胴体上面に沿って発達する境界層とインテークランプでの衝撃波との干渉によりバズが発生する可能性がある．これを回避するためにはダイバータ高さを高くすれば良いが，これは抵抗の増加を招く．そこで，ダイバータ高さについて設計値をノミナルとし，これをゼロとしたダイバータレス形態についても風洞試験を行った．作成されたインテークの空力性能データベースに基づきエンジン作動とのマッチングを行い，静粛超音速研究機の基本設計において設定されたエンジンの運用範囲内でインテークが適切に作動することを確認した．ただし，高マッハ数，高姿勢角ではバズ発生領域はエンジン運用範囲に近接しており，今後注視する必要がある．なお，バズの抑制に対しては補助ドア・バイパスドアが有効であり，総圧回復率や空間ディストーションの改善には境界層抽気が有効であることがわかった．","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"The air-intake of 3.5(sup th) configuration for the silent supersonic technology demonstrator, S3TD, having fixed geometry under a basic design policy, has been designed in Japan Aerospace Exploration Agency. The 3.5(sup th) configuration air-intake is mounted on the upper side of the fuselage, which implies that the boundary layer developing on the fuselage interacts with the shock wave at the ramp of the air-intake and causes the buzz in the supersonic regime. The supersonic wind tunnel test was conducted to make the aerodynamic database and to examine the condition on which the buzz occur. The diverter-less configuration as well as the nominal configuration was examined to enhance the effect of the boundary layer on the buzz. Results show that the 3.5(sup th) configuration air-intake operates normally within the engine operating boundary. However, at large angle of attack/sideslip and large Mach number the buzz occurs just outside the engine operating boundary. The buzz margin should be reviewed in the detailed design phase. Results also show that the bypass and auxiliary doors are effective to avoid the buzz and the bleeding system at the throat is effective to improve the pressure recovery rate and the level of inlet distortion.","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_19":{"attribute_name":"内容記述（英）","attribute_value_mlt":[{"subitem_description":"Physical characteristics: Original contains color illustrations","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0064696000","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-10-008","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"},{"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"},{"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  (APG)(JAXA)"},{"subitem_text_language":"en","subitem_text_value":"Supersonic Transport Team, Aviation Program Group, Japan Aerospace Exploration Agency  (APG)(JAXA)"},{"subitem_text_language":"en","subitem_text_value":"Supersonic Transport Team, Aviation Program Group, Japan Aerospace Exploration Agency  (APG)(JAXA)"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"上野, 篤史"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"渡辺, 安"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"赤塚, 純一"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Ueno, Atsushi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Watanabe, Yasushi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Akatsuka, Junichi","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":"64696000.pdf","filesize":[{"value":"12.4 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"64696000.pdf","url":"https://jaxa.repo.nii.ac.jp/record/2570/files/64696000.pdf"},"version_id":"e34cdf7b-2c6a-47ee-a293-0f14a5e05573"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"supersonic air-intake, aerodynamic performance, supersonic wind tunnel test","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性能取得超音速風洞試験","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性能取得超音速風洞試験"}]},"item_type_id":"3","owner":"1","path":["1222","1893"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"2570","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性能取得超音速風洞試験"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T09:19:51.588875+00:00"}