@inproceedings{oai:jaxa.repo.nii.ac.jp:00002947,
 author = {高橋, 政浩 and 野島, 清志 and 清水, 太郎 and 青野, 淳也 and 宗像, 利彦 and Takahashi, Masahiro and Nojima, Kiyoshi and Shimizu, Taro and Aono, Junya and Munakata, Toshihiko},
 book = {宇宙航空研究開発機構特別資料: 第50回流体力学講演会/第36回航空宇宙数値シミュレーション技術シンポジウム論文集, JAXA Special Publication: Proceedings of the 50th Fluid Dynamics Conference / the 36th Aerospace Numerical Simulation Symposium},
 month = {Feb},
 note = {第50回流体力学講演会/第36回航空宇宙数値シミュレーション技術シンポジウム (2018年7月4日-6日. 宮崎市民プラザ), 宮崎市, 宮崎, 50th Fluid Dynamics Conference /the 36th Aerospace Numerical Simulation Symposium (July 4-6, 2018. Miyazaki Citizen's Plaza), Miyazaki, Japan, RANS simulation corresponding to combustion tests of an ethylene-fueled scramjet combustor model was conducted by using a JAXA in-house solver LS-FLOW. For evaluation of the validity of the present CFD, the profiles of the combustion gas composition on the combustor exit plane predicted by the CFD were compared with experimental ones measured by using a gas sampling rake probe. Good agreement between the CFD and the gas sampling results was obtained at the center plane in the span-wise direction, but agreement was not good for the profiles at the other planes. Influence of both the turbulent Schmidt number and the C2H4-Air combustion mechanism used for the CFD on the numerical results were also examined. The turbulent Schmidt number showed strong influence on the numerical results and the small value of 0.3 resulted in better agreement with the experimental results than 0.89 in the present case. It was also shown that the difference of the combustion mechanisms did not show significant influence on the CFD results in the present case., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1830029018, レポート番号: JAXA-SP-18-005},
 pages = {159--164},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {LS-FLOW によるエチレン燃料スクラムジェット燃焼器流れの解析: 燃焼ガス組成の比較},
 volume = {JAXA-SP-18-005},
 year = {2019}
}