@techreport{oai:jaxa.repo.nii.ac.jp:00044973,
 author = {山田, 仁 and 上條, 謙二郎 and 渡辺, 光男 and 平田, 邦夫 and YAMADA, Hitoshi and KAMIJO, Kenjiro and WATANABE, Mitsuo and HIRATA, Kunio},
 month = {Jun},
 note = {The turbopump of a liquid rocket engine has to be able to operate with a low tank pressure in order to minimize the tank pressure. To provide this capability, the turbopump generally employs an inducer stage ahead of the main impeller. So it is important to predict the suction performance of the inducer itself. In the past the prediction of the net positive suction head(NPSH) of the inducer operating in cryogenic propellants, such as liquid hydrogen, liquid oxygen and so on, has often been investigated. However, little research has been done on the prediction of NPSH of inducers between different cryogenic liquids or different pump sizes. The present study deals with these problems. Two different inducers, one for liquid hydrogen, and the other for liquid oxygen, were tested in liquid nitrogen and another inducer was tested in liquid hydrogen for various rotative speeds, flow coefficients, and liquid temperatures. NPSH was measured for these three inducers for variopus flow conditions. The thermodynamic effect of cavitaion of liquid hydrogen and liquid nitrogen was compared. The measured values of NPSH in liquid hydrogen tests were in reasonable agreement with those predicted by using test data of liquid nitrogen., 資料番号: NALTR0716000, レポート番号: NAL TR-716},
 title = {ロケット用液体酸素および液体水素ポンプ・インデューサの吸込性能},
 year = {1982}
}