Faculty Profiles - KOUCHI Toshinori

MISC - KOUCHI Toshinori

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Numerical Prediction of RBCC Engine Pumping Performance Under Sea Level Static

河内俊憲, 苅田丈士, 富岡定毅

宇宙航空研究開発機構特別資料 JAXA-SP- ( 06-006 ) 2006

超音速燃焼器における燃料混合促進のための噴射孔形状に関する数値解析

平野昂志, 松尾亜紀子, 富岡定毅, 河内俊憲

数値流体力学シンポジウム講演論文集(CD-ROM) 20th 2006

ロケット複合エンジンのエジェクタモードにおける始動特性

河内俊憲, 櫻中登, 渡邊修一, 三谷徹, 富岡定毅

日本航空宇宙学会北部支部講演会講演論文集 2006 2006

Scramjet Performance Achieved in Engine Tests from M4 to M8 Flight Conditions

Tohru Mitani, Sadatake Tomioka, Takeshi Kanda, Nobuo Chinzei, Toshinori Kouchi

12th AIAA International Space Planes and Hypersonic Systems and Technologies 3 1 - 13 2004

Language：English Publisher：American Institute of Aeronautics and Astronautics

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%. By excluding boundary layer, an engine with a thick strut delivered a net thrust of 560 N and showed a thrust factor of 92% and a net thrust factor of 45%. The thrusts were limited by flow separation caused by engine combustion (termed as "engine unstart"). The starting characteristics was improved by boundary layer controls in M6 and M4 conditions. An engine with a thin strut doubled the thrust from 1620 N to 2460 N by the boundary layer bleeding in the M6 tests. The improved thrust factor was 60% 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% to 70%, the net thrust factor was increased from 32% to 55%. Studies required for improving the net performance were addressed.

DOI： 10.2514/6.2003-7009

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Scramjet Engine Performance Attained in RJTF Testing

三谷徹, 富岡定毅, 苅田丈士, 谷香一郎, 鎮西信夫, 河内俊憲

日本航空宇宙学会論文集 52 ( 600 ) 2004

SUBSCALE WIND TUNNELS AND SUPPLEMENTAL STUDIES OF SCRAMJET ENGINE TESTS.

三谷徹, 平岩徹夫, 苅田丈士, 志村隆, 渡辺修一, 樽川雄一, 河内俊憲, 北村英二郎, 八並知実

航空宇宙技術研究所報告 NAL-TR- ( 1458 ) 2003

Effects of Boundary-layer Bleeding on Scramjet Performance

河内俊憲, 三谷徹, 小寺正敏, 升谷五郎

日本機械学会流体工学部門講演会講演論文集 81st ( CD-ROM ) 2003

境界層抽気がスクラムジェット性能に及ぼす影響

河内俊憲, 三谷徹, 小寺正敏, 升谷五郎

日本機械学会流体工学部門講演会講演論文集 81st 2003

スクラムジェット燃焼の数値実験

三谷徹, 河内俊憲, 小寺正敏, 升谷五郎

燃焼シンポジウム講演論文集 41st 2003

レイノルズ数のスクラムジェットインレット性能に及ぼす影響

河内俊憲, 三谷徹, 小寺正敏, 升谷五郎

日本航空宇宙学会北部支部講演会講演論文集 2002 2002

Experiments of Extinction of Counterflow Twin Cylindrical Flames.

滝田謙一, 河内俊憲, 坂口成章, 布施顕太郎, JU Y

日本機械学会流体工学部門講演会講演論文集 79th ( 101-1010 ) 2001

スクラムジェットエンジンの燃焼性能見積り

三谷徹, 平岩徹夫, 河内俊憲, 升谷五郎

燃焼シンポジウム講演論文集 39th 2001

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