@techreport{oai:jaxa.repo.nii.ac.jp:00043876,
 author = {毛呂, 明夫 and 鈴木, 和雄 and MORO, Akio and SUZUKI, Kazuo},
 month = {Mar},
 note = {Polynomial approximations in three variables are presented for the calculation of theoretical performance parameters of the liquid rocket propellant combinations of liquid oxygen/liquid hydrogen,liquid oxygen/liquid methane,liquid oxygen/RP-1.liquid fluorine/liquid hydrogen,and nitrogen tetroxide/A-50.The parameters included are the adiabatic flame temperature,characteristic velocity,specific impulse,thrust coefficient,and specific heat ratios for both equilibrium and frozen compositions during expansion.The approximations are valid for wide ranges of mixture ratios,pressures from 10 to 80 atm,and nozzle area expansion ratios,from 10 to 100,or from 50 to 200.Maximum deviation between the approximated and exact theoretical values are shown.Performance parameters given by the polynomial approximations are graphically displayed., 資料番号: NALTM0293000, レポート番号: NAL TM-293},
 title = {ロケットプロペラントの理論性能: 多項近似式による表示},
 year = {1976}
}