Yue Zhou1, Pengfei Ju2,3,*
FDMP-Fluid Dynamics & Materials Processing, Vol.16, No.6, pp. 1273-1283, 2020, DOI:10.32604/fdmp.2020.09666
- 17 December 2020
Abstract The effects of the wall emissivity on aerodynamic heating in a scramjet
are analyzed. The supersonic turbulent combustion flow including radiation is
solved in the framework of a decoupled strategy where the flow field is determined first and the radiation field next. In particular, a finite difference method
is used for solving the flow while a DOM (iscrete ordinates method) approach
combined with a WSGGM (weighted sum of gray gases) model is implemented
for radiative transfer. Supersonic nonreactive turbulent channel flows are examined for a DLR hydrogen fueled scramjet changing parametrically the wall emissivity. The More >
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