研究者詳細 - 河内　俊憲

論文 - 河内　俊憲

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エンジン風洞における超音速流の閉塞査読

三谷徹, 宮島博, 谷香一郎, 河内俊憲, 櫻中登, 渡邊修一

日本航空宇宙学会論文集 55 ( 636 ) 43 - 50 2007年

Performance of a RBCC Combustor Operating in Ramjet Mode

Toshinori Kouchi, Kan Kobayashi, Kenji Kudo, Atsuo Murakami, Kanenori Kato, Tomioka Sadatake

42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 2006年7月

Evaluation of heat-flux on scramjet engine wall in Mach 6 flight condition

Shuichi Ueda, Masao Takegoshi, Toshinori Kouchi, Fumiei Ono, Toshihito Saito, Muneo Izumikawa

AIAA 57th International Astronautical Congress, IAC 2006 9 6344 - 6353 2006年

掲載種別：研究論文（国際会議プロシーディングス）出版者・発行元：American Institute of Aeronautics and Astronautics

Space transportation system uses the liquid hydrogen of the fuel as a coolant of the engine. Therefore, it is necessary to predict the heat flux to the engine wall in high accuracy for efficient cooling with a minimum coolant. However, the prediction of the heat flux to the scramjet engine combustor walls, is quite difficult due to complex interaction of flow and combustion. In this study, a sidewall-compression-type scramjet engine was tested under Mach 6 flight conditions using Ramjet Engine Test Facility. The heat flux was measured using water-cooled heat-flux meters installed on the sidewall within the combustor sections. The experimental results were compared with CFD analysis of the whole engine to predict heat flux distribution on the engine wall. The numerical results of wall pressure distribution showed good agreement with the experimental data. However, the experimental results of heat flux were extremely higher than the numerical results due to the radiation heating which was not considered in the CFD analysis. Based on the results, the average heat flux of the sub-scale scramjet engine with 300 K isothermal walls was 1 MW/m2 in the stoichiometric fuel rate at Mach 6 flight conditions.

DOI： 10.2514/6.iac-06-c4.5.04

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Performance Comparison of Combined Fuel Injection Methods in a Staged-Combustion Scramjet Engine 査読

Ueda, S, Tomioka, S, Kouchi, T, Kobayashi, K, Kudo, K, Kato, K

Proceedings of the 25th International Symposium on Space Technology and Science 121 - 126 2006年

Transition of Combustion Modes in a Scramjet Engine 査読

Kouchi, T, Mitani, T, Tomioka, S, Ueda, S

Proceedings of the 25th International Symposium on Space Technology and Science 107 - 114 2006年

Flame structures and combustion efficiency computed for a Mach 6 scramjet engine 査読

Mitani, T, Kouchi, T

Combustion and Flame 142 ( 3 ) 187 - 196 2005年8月

Numerical simulations in scramjet combustion with boundary-layer bleeding 査読

Kouchi, T, Mitani, T, Masuya, G

Journal of Propulsion and Power 21 ( 4 ) 642 - 649 2005年7月

Problems of Numerical Diffusion Found in Scramjets

Toshinori Kouchi, Tohru Mitani, Goro Masuya

AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference 2005年5月

Heat Flux Prediction for Scramjet Engines, - Accuracy of Reynolds Analogy on Scramjet Internal Walls 査読

Kouchi, T, Mitani, T, Hiraiwa, T, Kodera, M, Masuya, G

Proceedings of the 24th International Symposium on Space Technology and Science 20 - 26 2004年

RJTF試験におけるスクラムジェット性能達成度査読

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 ) 1 - 9 2004年

Numerical Experiments of Scramjet Combustion with Boundary-Layer Bleeding

Toshinori Kouchi, Tohru Mitani, Masatoshi Kodera, Goro Masuya

12th AIAA International Space Planes and Hypersonic Systems and Technologies 2003年12月

抗力測定によるスクラムジェットの推力性能見積り査読

河内俊憲, 三谷徹, 平岩徹夫, 富岡定毅, 升谷五郎

日本航空宇宙学会論文集 51 ( 595 ) 403 - 411 2003年

Effects of Reynolds Number on Scramjet Inlet Performance 査読

Kouchi, T, Mitani, T, Kodera, M, Masuya, G

Proceedings of the 23rd International Symposium on Space Technology and Science 21 2412 - 2417 2002年

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