@techreport{oai:jaxa.repo.nii.ac.jp:00044948,
 author = {橋本, 亮平 and 上絛, 謙二郎 and 渡辺, 義明 and 長谷川, 敏 and 藤田, 敏彦 and HASHIMOTO, Ryohei and KAMIJO, Kenjiro and WATANABE, Yoshiaki and HASEGAWA, Satoshi and FUJITA, Toshihiko},
 month = {Dec},
 note = {The aerodynamic performance evaluation of the pump-drive turbines for a 10 ton thrust liquid oxygen and liquid hydrogen (LOX and LH2) gas generator cycle propulsion system, which has dual-shaft series turbines, was tested mainly using cold nitrogen gas. At design equivalent speed and pressure ratio, the LOX turbine static efficiency was about 35 percent compared to the design value of 32.8 percent. The LH2 turbine static efficiency was very close to the design value of 45 percent. Equivalent weight flow of both the LOX and LH2 turbines was greater than design value. The specifications of the turbines were changed in order to utilize the present test results as much as possible. No aerodynamic design modifications were made on either turbine. So the aerodynamic performance of the LOX and LH2 turbines for the LE-5 engine is almost the same as the present results., 資料番号: NALTR0691000, レポート番号: NAL TR-691},
 title = {PERFORMANCE EVALUATION OF LOX AND LH2 TURBOPUMP TURBINES FOR A 10 TON THRUST LOX/LH2 ROCKET ENGINE},
 year = {1981}
}