@article{oai:jaxa.repo.nii.ac.jp:00035152,
 author = {岩間, 彬 and 山崎, 毅六 and 菊地, 健 and IWAMA, Akira and YAMAZAKI, Kiroku and KIKUCHI, Ken},
 issue = {3},
 journal = {東京大学航空研究所集報},
 month = {Sep},
 note = {ヒドラジン-三フッ化塩素系液体ロケット・エンジンの設計に必要な理論性能および熱力学的諸数値を東大理学部のパラメトロン電子計算機PC-1を使用して理論的に求めた.その結果(1)ヒドラジン-三フッ化塩素系推進剤の理論性能を得,燃焼室圧20気圧で最高理論比推力247.6秒が混合比約1.9の点で得られた.(2)熱損失を考慮した場合でも燃焼温度が決定できるダイアグラム作成した.(3)種々の温度と混合比に対する比容積,比熱,比熱比,および平均分子量を提出した., The results of calculation for the theoretical performance and various thermodynamic data of hydrazine-chlorine trifluoride hypergolic propellant system have been described. The calculation was performed with the parametron computer, PC-1 at the Faculty of Science, University of Tokyo. The results obtained were summarized as follows; (1) The theoretical performances of N_2H_2-CIF_3 propellant system were obtained, and the maximum theoretical specific impulse was 247.6 sec. at mixture ratio of 1.9 (Pc=20atm.). (2) A diagram for determination of the combustion temperature was obtained and it could be applicable even in the case of taking account of heat loss. (3) The chart concerned to specific volume, heat capacity, ratio of specific heat and mean molecular weight of combustion products at various tempeatures and mixture ratios was presented., 資料番号: SA4135034000},
 pages = {179--187},
 title = {ヒドラジン-三フッ化塩素系推進剤の理論性能},
 volume = {3},
 year = {1962}
}