@inproceedings{oai:jaxa.repo.nii.ac.jp:00038251,
 author = {清水, 太郎 and 宮島, 博 and 中橋, 和博 and Shimizu, Taro and Miyajima, Hiroshi and Nakahashi, Kazuhiro},
 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 = {The purpose of this study is the numerical investigation of the origin of the side-load generated in the LE-7A rocket engine nozzle during the start-up and shut-down transient operation. So far, the origin of the side-load causing the maximum load of the actuator is considered to be due to the gap for the film cooling port, which slows down the movement of separation line followed by a sudden and large shift. This mechanism with a 3D flow instability would explain the non-axisymmetric flow pattern, namely, the side-load. Several authors have explained the above scenario by the observation of the sea level tests and mainly 2D axisymmetric numerical simulation. This study focuses on the numerical verification of the above assumption and the quantitative evaluation of the side-load by 3D numerical simulation. The numerical method to solve the Navier-Stokes equations on the unstructured hybrid grid was developed using a finite volume cell vertex scheme and the LU-SGS implicit time integration algorism. The results show the characteristic flow pattern with a non-axisymmetric separation line between the gap and the nozzle end. The side-load calculated by the numerical results is considered to be nearly maximum as long as the flow pattern is FSS (free shock separation), and is comparable to the experimental data. Possible errors of the numerical calculation were also estimated., 資料番号: AA0045948030, レポート番号: NAL SP-57},
 pages = {166--171},
 publisher = {航空宇宙技術研究所, National Aerospace Laboratory (NAL)},
 title = {ロケットエンジンノズル内部流れの数値計算},
 volume = {57},
 year = {2003}
}