Scramjet performance achieved in engine tests from M4 to M8 flight conditions

Material type: 文書・図像類

Author: 三谷, 徹ほか

Publisher: 宇宙航空研究開発機構

Publication date: 2004-03-25

Material Format: Digital

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Note (General)：: Thrust performances of scramjet engines were compared with theoretical values to quantify the progress in engine performances (defined as achievement ...

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Material Type: 文書・図像類
Title: Scramjet performance achieved in engine tests from M4 to M8 flight conditions
Author/Editor: 三谷, 徹
富岡, 定毅
苅田, 丈士
鎮西, 信夫
河内, 俊憲
Mitani, Toru
Tomioka, Sadatake
Kanda, Takeshi
Chinzei, Nobuo
Kochi, Toshinori
Author Heading: 三谷, 徹
富岡, 定毅
苅田, 丈士
鎮西, 信夫
河内, 俊憲
Mitani, Toru
Tomioka, Sadatake
Kanda, Takeshi
Chinzei, Nobuo
Kochi, Toshinori
Publication, Distribution, etc.: 宇宙航空研究開発機構
Publication Date: 2004-03-25
Publication Date (W3CDTF): 2004-03-25
Alternative Title: M4からM8におけるスクラムジェットエンジン試験における性能達成度
Periodical title: 宇宙航空研究開発機構研究開発報告 = JAXA Research and Development Report
No. or year of volume/issue: JAXA-RR-03-020E
Volume: JAXA-RR-03-020E
ISSN (Periodical Title): ISSN : 1349-1113
Text Language Code: eng
Subject Heading: スクラムジェットエンジン
性能試験
マッハ数
境界層
推力
空気捕捉比
化学量論比
scramjet engine
performance test
Mach number
boundary layer
thrust
air capture ratio
stoichiometric ratio
Target Audience: 一般
Note (General): Thrust performances of scramjet engines were compared with theoretical values to quantify the progress in engine performances (defined as achievement factors, or factors) from Mach (termed as M) 4 to M8 flight conditions. An engine with a ramp produced a net thrust of 215 N under the M8 tests and a comparison of a theoretical thrust yielded a thrust achievement factor of 51 percent. By excluding boundary layer, an engine with a thick strut delivered a net thrust of 560 N and showed a thrust factor of 92 percent and a net thrust factor of 45 percent. The thrusts were limited by flow separation caused by engine combustion (termed as engine unstart). The starting characteristics were improved by boundary layer controls in M6 and M4 conditions. An engine with a thin strut doubled the thrust from 1,620 N to 2,460 N by the boundary layer bleeding in the M6 tests. The improved thrust factor was 60 percent at the stoichiometric H2 condition. Under M4 tests, the net thrust was tripled by the bleed and a two-staged injection of H2. As results, the thrust factor was raised from 53 percent to 70 percent, the net thrust factor was increased from 32 percent to 55 percent. Studies required for improving the net performance were addressed.
ISSNの誤記: 1349-1148
Incorrect ISSN: 1349-1148
資料番号: AA0047412000
レポート番号: JAXA-RR-03-020E
Source: https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=2400&item_no=1&attribute_id=31&file_no=1
https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=2400&item_no=1&attribute_id=31&file_no=1
Access Restrictions: 限定公開
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