@techreport{oai:jaxa.repo.nii.ac.jp:00045222,
 author = {渡辺, 義明 and 渡辺, 光男 and 上條, 謙二郎 and WATANABE, Yoshiaki and WATANABE, Mitsuo and KAMIJO, Kenjiro},
 month = {Mar},
 note = {For more than ten years, several small cryogenic pumps for liquid rocket engines have been made for purposes of research and development by the National Aerospace Laboratory and the National Space Development Agency of Japan. These pumps were made for use with liquid oxygen (LOX) and liquid hydrogen (LH2) feed pumps. They have very small impellers and are characterized by high speed and high head. The main design characteristics of these pumps are as follows: stage specific speeds of from 0.0319 to 0.0766, flow rates from 0.016 to 0.0525 m3/s, pressure rises from 4.9 to 26 MPa, rotational speeds from 16,500 to 80,000 rpm and impeller diameters from 0.083 to 0.146 m. These pumps were tested using water, LOX, liquid nitrogen (LN2) and liquid hydrogen as the pump fluids. The present paper not only focuses on overall performance factors such as efficiency and head/flow characteristics, but also on suction performance of these pumps., 資料番号: NALTR0963000, レポート番号: NAL TR-963},
 title = {Performance of Small High Speed Rocket Pumps},
 year = {1988}
}