摘要
Turbulent combustion in a DLR (German Aerospace Center) Scramjet engine was simulated using the newly-proposed Partially Resolved Numerical Simulation (PRNS) procedure. The PRNS procedure uses temporal filtering to define large-scale turbulence, and the model developed to account for unresolved scales is grid independent. No problem about inner commutation error and inconsistencies will arise from the PRNS, while such issues are of concern in traditional Large Eddy Simulation (LES) methods. The mean results have good agreement with the experiment data and the flow structures with small scales are well resolved.
Turbulent combustion in a DLR （German Aerospace Center） Scramjet engine was simulated using the newly-proposed Partially Resolved Numerical Simulation （PRNS） procedure. The PRNS procedure uses temporal filtering to define large-scale turbulence, and the model developed to account for unresolved scales is grid independent. No problem about inner commutation error and inconsistencies will arise from the PRNS, while such issues are of concern in traditional Large Eddy Simulation （LES） methods. The mean results have good agreement with the experiment data and the flow structures with small scales are well resolved.
基金
Project supported by the National Natural Science Foundation of China (No. 90405003)
the China Postdoctoral Science Founda-tion (No. 20060390339)
关键词
超音速冲压喷射装置
模拟技术
容积
流体力学
Scramjet, Turbulent combustion, Unstructured grid, Finite volume method
