@Article{CiCP-18-1181,
author = {Juan-Chen Huang, Yu-Hsuan Lai, Jeng-Shan Guo and Jaw-Yen Yang},
title = {Simulation of Two-Dimensional Scramjet Combustor Reacting Flow Field Using Reynolds Averaged Navier-Stokes WENO Solver},
journal = {Communications in Computational Physics},
year = {2018},
volume = {18},
number = {4},
pages = {1181--1210},
abstract = {<p style="text-align: justify;">The non-equilibrium chemical reacting combustion flows of a proposed long
slender scramjet system were numerically studied by solving the turbulent Reynolds
averaged Navier-Stokes (RANS) equations. The Spalart-Allmaras one equation turbulence
model is used which produces better results for near wall and boundary layer
flow field problems. The lower-upper symmetric Gauss-Seidel implicit scheme, which
enables results converge efficiently under steady state condition, is combined with the
weighted essentially non-oscillatory (WENO) scheme to yield an accurate simulation
tool for scramjet combustion flow field analysis. Using the WENO schemes high-order
accuracy and its non-oscillatory solution at flow discontinuities, better resolution of
the hypersonic flow problems involving complex shock-shock/shock-boundary layer
interactions inside the flow path, can be achieved. Two types of scramjet combustor
with cavity-based and strut-based fuel injector were considered as the testing models.
The flow characteristics with and without combustion reactions of the two types of combustor models were studied with a transient hydrogen/oxygen combustion model.
The detailed results of aerodynamic data are obtained and discussed, moreover, the
combustion properties of varying the equivalent ratio of hydrogen, including the concentration
of reacting species, hydrogen and oxygen, and the reacting products, water,
are demonstrated to study the combustion process and performance of the combustor.
The comparisons of flow field structures, pressure on wall and velocity profiles
between the experimental data and the solutions of the present algorithms, showed
qualitatively as well as the quantitatively in good agreement, and validated the adequacy
of the present simulation tool for hypersonic scramjet reacting flow analysis.</p>},
issn = {1991-7120},
doi = {https://doi.org/10.4208/cicp.190115.210715s},
url = {http://global-sci.org/intro/article_detail/cicp/11065.html}
}