@inproceedings{oai:jaxa.repo.nii.ac.jp:00038252,
 author = {山西, 伸宏 and 加藤, 千幸 and 宮島, 博 and 辻本, 良信 and 吉田, 義樹 and Yamanishi, Nobuhiro and Kato, Chisachi and Miyajima, Hiroshi and Tsujimoto, Yoshinobu and Yoshida, Yoshiki},
 book = {航空宇宙技術研究所特別資料: 航空宇宙数値シミュレーション技術シンポジウム2002論文集, Special Publication of National Aerospace Laboratory: Proceedings of Aerospace Numerical Simulation Symposium 2002},
 month = {Mar},
 note = {Large eddy simulation of a rocket turbopump inducer at design and off-design conditions is presented. The computation takes full account of the interaction between the rotating inducer and the stationary casing by using a multi-frame-of-reference dynamic overset grid approach. A streamline-upwind finite element formulation with second-order accuracy both in time and space is used to discretize the governing equation. It is implemented in parallel by a domain-decomposition-programming model. The basic design of the inducer is similar to the one used in the LE-7 rocket engine liquid oxygen turbopump. It has three helical blades with 95.5 deg sweep back leading edge and a tip diameter of 149.8 mm. The inlet blade angle is 7.5 deg and the discharge blade angle is 9.0 deg at the tip. Internal flow of an inducer is simulated and compared with water tunnel experiments at design (phi = 0.078) and off-design conditions (phi = 0.05 and 0.09). Although some difference can be seen at low flow coefficients, the overall head-flow characteristics of computed results show good agreement with experiments. Such results show that the applied LES code can be used as a design tool for rocket turbopump inducers., 資料番号: AA0045948031, レポート番号: NAL SP-57},
 pages = {172--177},
 publisher = {航空宇宙技術研究所, National Aerospace Laboratory (NAL)},
 title = {インデューサにおける非定常流れのLES解析},
 volume = {57},
 year = {2003}
}