静止から極超音速域までの複合エンジンインレット性能改善試験について

Material type: 文書・図像類

Author: 谷, 香一郎ほか

Publisher: 宇宙航空研究開発機構

Publication date: 2006-01-20

Material Format: Digital

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Note (General)：: A designing concept for the inlet of the combined cycle engine was explored in the current study. The models designed by the concept were tested in se...

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Material Type: 文書・図像類
Title: 静止から極超音速域までの複合エンジンインレット性能改善試験について
Author/Editor: 谷, 香一郎
苅田, 丈士
加藤, 周徳
桜中, 登
渡辺, 修一
Tani, Koichiro
Kanda, Takeshi
Kato, Kanenori
Sakuranaka, Noboru
Watanabe, Shuichi
Author Heading: 谷, 香一郎
苅田, 丈士
加藤, 周徳
桜中, 登
渡辺, 修一
Tani, Koichiro
Kanda, Takeshi
Kato, Kanenori
Sakuranaka, Noboru
Watanabe, Shuichi
Publication, Distribution, etc.: 宇宙航空研究開発機構
Publication Date: 2006-01-20
Publication Date (W3CDTF): 2006-01-20
Alternative Title: Performance improvement of the combined cycle engine inlets from ground to hypersonic speed
Periodical title: 宇宙航空研究開発機構特別資料: 平成16年度総合技術研究本部宇宙領域宇宙科学研究本部合同研究成果報告書:宇宙輸送系基盤技術 = JAXA Special Publication: FY2004 Report of Joint Research Achievements of the Space Division of Institute of Aerospace Technology and Institute of Space and Astronautical Science: Basic Technologies of Space Transportation Systems
No. or year of volume/issue: JAXA-SP-05-010
Volume: JAXA-SP-05-010
Pages: 63-68
ISSN (Periodical Title): ISSN : 1349-113X
Text Language Code: jpn
Subject Heading: 構造設計
インレット流
複合サイクルエンジン
ロケットエンジン設計
風洞試験
圧力抵抗
推薬燃焼
湾曲衝撃構造
衝撃波
structural design
inlet flow
combined cycle engine
rocket engine design
wind tunnel test
pressure drag
propellant combustion
skewed shock structure
shock wave
Target Audience: 一般
Note (General): A designing concept for the inlet of the combined cycle engine was explored in the current study. The models designed by the concept were tested in several wind tunnels, ranging from subsonic to hypersonic air speed. The experimental results showed the decrease of the pressure drag in sub/transonic regime. In supersonic condition, the new model proved the high starting capability. However, in hypersonic range, the inlets lost more mass flow than expected, due to the skewed shock structure. Further studies will be required to establish optimized geometry of the inlet.
資料番号: AA0049056014
レポート番号: JAXA-SP-05-010
Access Restrictions: 限定公開
Periodical Title (NCID): AA11984031
https://ci.nii.ac.jp/ncid/AA11984031
Data Provider (Database): 国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
https://irdb.nii.ac.jp
Original Data Provider (Database): 宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ