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Numerical investigation on supersonic combustion in SCRAMJET engine by FaSTAR
- 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<br />49th Fluid Dynamics Conference /the 35th Aerospace Numerical Simulation Symposium (June 28-30, 2017. National Olympics Memorial Youth Center), Shibuya-ku, Tokyo, Japan<br />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.<br />形態: カラー図版あり<br />Physical characteristics: Original contains color illustrations<br />資料番号: AA1730011022<br />レポート番号: JAXA-SP-17-004
Details
- 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