Numerical Investigation of Combustion Instabilities in a Rocket Combustion Chamber with Supercritical Injection Using a Hybrid RANS/LES Method
Author:
Affiliation:
1. German Aerospace Center (DLR)
Publisher
American Institute of Aeronautics and Astronautics
Reference27 articles.
1. High order numerical simulation of the thermal load on a lobed strut injector for scramjet applications
2. Supercritical LOX/Hydrogen Rocket Combustion Investigations Using Optical Diagnostics
3. 5Seidl, M., Numerische Simulation von Raketenbrennkammern mit transkritischer Einspritzung, Ph.D. thesis,Universität Stuttgart, 2018.
Cited by 3 articles. 订阅此论文施引文献 订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献
1. Flame dynamics of an injection element operated with LOX/H2, LOX/CNG and LOX/LNG in a sub- and supercritical rocket combustor with large optical access;International Journal of Spray and Combustion Dynamics;2023-05-19
2. Flame characteristics of a high-pressure LOX/H2 rocket combustor with large optical access;Case Studies in Thermal Engineering;2021-12
3. Rocket Combustion Chamber Simulations Using High-Order Methods;Notes on Numerical Fluid Mechanics and Multidisciplinary Design;2020-10-27
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