{"created":"2023-06-19T10:30:12.742739+00:00","id":10425,"links":{},"metadata":{"_buckets":{"deposit":"e27476db-b4e4-47ba-823f-404fb6b6ab74"},"_deposit":{"created_by":18,"id":"10425","owners":[18],"pid":{"revision_id":0,"type":"depid","value":"10425"},"status":"published"},"_oai":{"id":"oai:muroran-it.repo.nii.ac.jp:00010425","sets":["216:290","216:408:340","46"]},"author_link":["58442","51226","9542","747","801","58443"],"item_79_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2016","bibliographicIssueDateType":"Issued"},"bibliographicIssueNumber":"30","bibliographicVolumeNumber":"14","bibliographic_titles":[{"bibliographic_title":"TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES","bibliographic_titleLang":"en"}]}]},"item_79_description_23":{"attribute_name":"フォーマット","attribute_value_mlt":[{"subitem_description":"application/pdf","subitem_description_type":"Other"}]},"item_79_description_7":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"With the aims of creating and validating innovative fundamental technologies for high-speed atmospheric flights, a small scale supersonic flight experiment vehicle is designed as a flying test bed. An aerodynamic configuration is proposed for the 2nd-generation vehicle with a cranked-arrow main wing and a single Air Turbo Ramjet Gas-generator-cycle (ATR-GG) engine. Its longitudinal, lateral, and control surface aerodynamics are characterized through intensive wind-tunnel tests. They are found to be quite moderate except that the directional stability deteriorates severely at large angles of attack and side slip, and that the elevon deflections for roll control cause adverse yaw. These aerodynamic anomalies will result in a tendency of roll reversal at large angles of attack. It can be prevented to some extent by coordinated rudder deflections. In addition, necessity of transonic drag reduction is clarified through thrust margin and flight capability analyses. Probability of 5 to 20 % drag reduction in the transonic regime (Mach 0.8 to 1.2) is demonstrated by configuration modification on the basis of the area rule at Mach 1.1.","subitem_description_language":"en","subitem_description_type":"Abstract"}]},"item_79_link_17":{"attribute_name":"出版者版へのリンク","attribute_value_mlt":[{"subitem_link_text":"10.2322/tastj.14.Pg_1","subitem_link_url":"https://doi.org/10.2322/tastj.14.Pg_1"}]},"item_79_link_5":{"attribute_name":"室蘭工業大学研究者データベースへのリンク","attribute_value_mlt":[{"subitem_link_text":"溝端 一秀（MIZOBATA Kazuhide）","subitem_link_url":"http://rdsoran.muroran-it.ac.jp/html/100000207_ja.html"}]},"item_79_publisher_11":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"JAPAN SOC AERONAUT SPACE 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