@techreport{oai:jaxa.repo.nii.ac.jp:00045312,
 author = {熊谷, 達夫 and 植田, 修一 and 佐藤, 政裕 and 須藤, 孝幸 and 宮島, 博 and 渡辺, 篤太郎 and 山川, 正紀 and KUMAGAI, Tatsuo and UEDA, Shuichi and SATO, Masahiro and SUDO, Takayuki and MIYAJIMA, Hiroshi and WATANABE, Atsutaro and YAMAKAWA, Masanori},
 month = {Feb},
 note = {Performance tests of high density hydrocarbon fuel were conducted with a small rocket engine. The densities of the fuel examined, RJ-1J, HDF-1, and HDF-3 were 0.851, 0.996, and 1.006 respectively. The RJ-1J, which is used for the Japanese H-1 rocket, served as a reference for comparison. The thrust of the rocket engine was 490N at a chamber pressure of 2.94 MPa and a nozzle area ratio of 5:1. The thrust chamber was water cooled, and gaseous oxygen was used as the oxidizer. To simulate a duel fuel condition, a small amount of gaseous hydrogen(2％ of hydrocarbon fuel) was added to the combustion chamber. The effect of the amount of hydrogen addition on specific impulse was also tested. Measured peak vacuum specific impulses for RJ-1J, HDF-1, and HDF-3 respectively were 291, 290, and 287s, which is in qualitative accord with theoretical prediction. Specific impulse increased with the amount of hydrogen added as predicted. However, energy release efficiency was not affected appreciably, since it was very near to 100％ at the conditions tested. It was concluded that two kinds of high density fuel tested have acceptable performances and properties for dual fuel engines. An engine specific impulse may be extrapolated from the present experiment to be 345 s at a 1000kN thrust and 10 MPa chamber pressure level., 資料番号: NALTR1053000, レポート番号: NAL TR-1053},
 title = {Specific Impulse Comparison of High Density Hydrocarbon Fuel Burned with Oxygen},
 year = {1990}
}