Numerical investigation on supersonic combustion in SCRAMJET engine by FaSTAR

Authors :: Toyonaga, Rui
Yamamoto, Himeko
Mizobuchi, Yasuhiro
Sato, Tetsuya
Source :: 宇宙航空研究開発機構特別資料: 第49回流体力学講演会/第35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 49th Fluid Dynamics Conference / the 35th Aerospace Numerical Simulation Symposium. :143-146
Publication Year :: 2017
Publisher :: 宇宙航空研究開発機構(JAXA), 2017.
Abstract: 第49回流体力学講演会/第35回航空宇宙数値シミュレーション技術シンポジウム (2017年6月28日-30日. 国立オリンピック記念青少年総合センター), 渋谷区, 東京 49th Fluid Dynamics Conference /the 35th Aerospace Numerical Simulation Symposium (June 28-30, 2017. National Olympics Memorial Youth Center), Shibuya-ku, Tokyo, Japan In this study, the implementation of the combustion calculation code (flamelet approach) for a complex combustion field to a density-based fluid analysis solver, FaSTAR is conducted. With this calculation code, numerical exploration of non-reacting and reacting flow field of hydrogen fueled scramjet combustor is presented. The interaction between combustion and complex shock structures are well captured in the simulation. 形態: カラー図版あり Physical characteristics: Original contains color illustrations 資料番号: AA1730011022 レポート番号: JAXA-SP-17-004

Language :: Japanese
ISSN :: 24332232
Database :: OpenAIRE
Journal :: 宇宙航空研究開発機構特別資料: 第49回流体力学講演会/第35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 49th Fluid Dynamics Conference / the 35th Aerospace Numerical Simulation Symposium
Accession number :: edsair.jairo.........fbe4c683371d6d0d60d9b05f12d7ce1b