@techreport{oai:jaxa.repo.nii.ac.jp:00044919,
 author = {宮島, 博 and 毛呂, 明夫 and 日下, 和夫 and 中橋, 和博 and 黒田, 行郎 and 熊谷, 達夫 and 木皿, 且人 and 鎌田, 真 and 佐藤, 政裕 and 阿部, 登 and 勝田, 秀明 and MIYAJIMA, Hiroshi and MORO, Akio and KUSAKA, Kazuo and NAKAHASHI, Kazuhiro and KURODA, Yukio and KUMAGAI, Tatsuo and KISARA, Katsuto and KAMATA, Makoto and SATO, Masahiro and ABE, Noboru and KATSUTA, Hideaki},
 month = {Apr},
 note = {The performance of a thrust chamber with a nozzle whose nominal expansion area ratio was 140:1 was evaluated under environmental pressure of 8 to 13 torr. The nominal vacuum thrust of the chamber was 400kgf at a chamber pressure of 35.5kg/cm2, abs. Measurements were also made of the wall static pressure distribution, wall heat flux distribution over the heat sink nozzle extention, and of the Pitot pressure distribution at the nozzle exit plane. The effects of hydrogen inlet temperature and chamber pressure on the thrust chamber performance was not significant over a temperature range of 120 to 140 K and a chamber pressure range of 30 to 39kg/cm2, abs. In the mixture ratio range of 4.5 to 6.5, characteristic velocity and vacuum specific impulse Ispv decreased with mixture ratio, while thrust coefficient increased slowly with mixture ratio in the range of 4.5 to 6.0. The measured Ispv at the mixture ratio of 5.5 was about 450kgf・s/kg. Measured performance values were compared with analytical prediction. The predicted vlue was too low apparently because of large calculated boundary layer loss. It was also shown that the stronger dependence of Ispv on the mixture ratio compared with the one-dimensional equilibrium value was partly attributable to chemical kinetic loss. The measured nozzle wall pressure and the nozzle exit Mach number distribution were in reasonable agreement with predicted values calculated by the two-dimensional nozzle analysis computer program developed by the authors. The measured nozzle wall heat flux in the nozzle area ratio 75 to 140 was 11 to 6 cal/(cm2・s) decreasing with area ratio in approximate tendencial agreement with either turbulent boundary layer calculation or simplified Bartz equation., 資料番号: NALTR0662000, レポート番号: NAL TR-662},
 title = {EXPERIMENTAL PERFORMANCE OF A SMALL LOX/H2 THRUST CHAMBER WITH A HIGH AREA RATIO NOZZLE(1)},
 year = {1981}
}