@inproceedings{oai:jaxa.repo.nii.ac.jp:00006168,
 author = {坪井, 伸幸 and 伊藤, 隆 and 宮島, 博 and Tsuboi, Nobuyuki and Ito, Takashi and Miyajima, Hiroshi},
 book = {宇宙航空研究開発機構特別資料: 航空宇宙数値シミュレーション技術シンポジウム2005論文集, JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2005},
 month = {Feb},
 note = {LOX/LH2 subscale rocket nozzle flow fields are computationally simulated using three-dimensional compressible Navier-Stokes equations. The area ratio of the nozzle is 140 and film coolant hydrogen gases are injected from 30 film cooling holes which are distributed circumferentially at the area ratio of 13. The experimental nozzle throat Reynolds number indicates that the boundary layer of the nozzle is in its transition region as the size of the nozzle is small. Both the turbulent and laminar computations are carried out to investigate the effect of the boundary layer conditions to the nozzle performance. The computed results show that the structure of the separated flow down stream of the film cooling injection significantly changes between the turbulent and laminar conditions. Since clear difference in performance between the laminar and turbulent conditions are also shown, the computed result confirms that the experiment boundary layer condition is in its transition region. The nozzle wall temperature also influences the nozzle performance and the computed nozzle performance shows rather laminar flow performance when the film coolant temperature and the nozzle wall temperatures are set to be close., 資料番号: AA0049212035, レポート番号: JAXA-SP-05-017},
 pages = {209--214},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {フィルム冷却を考慮した液酸・液水ロケットエンジン性能解析},
 volume = {JAXA-SP-05-017},
 year = {2006}
}