| Item type |
学術雑誌論文 / Journal Article.(1) |
| 公開日 |
2020-01-22 |
| 書誌情報 |
en : TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN
巻 17,
号 2,
p. 127-133,
発行日 2019
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| タイトル |
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|
タイトル |
Drag Reduction on the Basis of the Area Rule of the Small-scale Supersonic Flight Experiment Vehicle Being Developed at Muroran Institute of Technology |
|
言語 |
en |
| 言語 |
|
|
言語 |
eng |
| キーワード |
|
|
言語 |
en |
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主題Scheme |
Other |
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主題 |
Supersonic |
| キーワード |
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|
言語 |
en |
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主題Scheme |
Other |
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主題 |
Drag Reduction |
| キーワード |
|
|
言語 |
en |
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主題Scheme |
Other |
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主題 |
Area Rule |
| キーワード |
|
|
言語 |
en |
|
主題Scheme |
Other |
|
主題 |
Wave Drag Analysis |
| キーワード |
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|
言語 |
en |
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主題Scheme |
Other |
|
主題 |
Wind Tunnel Test |
| 資源タイプ |
|
|
資源タイプ識別子 |
http://purl.org/coar/resource_type/c_6501 |
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資源タイプ |
journal article |
| アクセス権 |
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|
アクセス権 |
open access |
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アクセス権URI |
http://purl.org/coar/access_right/c_abf2 |
| 著者 |
山﨑, 優樹
溝端, 一秀
東野, 和幸
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| 室蘭工業大学研究者データベースへのリンク |
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表示名 |
溝端 一秀(MIZOBATA Kazuhide) |
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URL |
http://rdsoran.muroran-it.ac.jp/html/100000207_ja.html |
| 抄録 |
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内容記述タイプ |
Abstract |
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内容記述 |
A small-scale supersonic flight experiment vehicle (OWASHI) is being developed at Muroran Institute of Technology as a flying testbed for verification of innovative technologies for high speed atmospheric flights which are essential to next-generation aerospace transportation systems. The second-generation configuration M2011 of the vehicle with a single Air Turbo Ramjet Gas-generator-cycle (ATR-GG) engine has been proposed. Its transonic thrust margin has been predicted to be insufficient, therefore drag reduction in the transonic regime is quite crucial for attainability of supersonic flights. In this study, we propose configuration modifications for drag reduction on the basis of the so-called area rule, and assess their effects through wave drag analysis, wind tunnel tests, and CFD analysis. As a result, the area-rule-based configurations have less drag than the baseline configuration M2011. However, the effects of the proposed bottleneck on the fuselage below the main wing are smaller than predicted. It would be caused by the drag due to separation and shocks around the bottleneck. It is necessary to redesign the area-rule-based bottleneck to be smoother. |
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言語 |
en |
| 出版者 |
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出版者 |
JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES |
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言語 |
en |
| 出版者版へのリンク |
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表示名 |
10.2322/tastj.17.127 |
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URL |
https://doi.org/10.2322/tastj.17.127 |
| DOI |
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関連タイプ |
isVersionOf |
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識別子タイプ |
DOI |
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関連識別子 |
10.2322/tastj.17.127 |
| 論文ID（NAID） |
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関連タイプ |
isVersionOf |
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識別子タイプ |
NAID |
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関連識別子 |
130007607485 |
| 日本十進分類法 |
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主題Scheme |
NDC |
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主題 |
538 |
| ISSN |
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収録物識別子タイプ |
EISSN |
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収録物識別子 |
1884-0485 |
| 権利 |
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|
言語 |
en |
|
権利情報 |
© 2019 JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES |
| 著者版フラグ |
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出版タイプ |
AM |
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出版タイプResource |
http://purl.org/coar/version/c_ab4af688f83e57aa |
| フォーマット |
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内容記述タイプ |
Other |
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内容記述 |
application/pdf |
TJSASS_17_2_127_133 (1.6 MB)
