TY - EJOU
AU - Wang, Jingying
AU - Han, Fangzhou
AU - Lei, Li
AU - Lee, Chunhian
TI - Numerical Study of High-Temperature Nonequilibrium Flow around Reentry Vehicle Coupled with Thermal Radiation
T2 - Fluid Dynamics \& Materials Processing
PY - 2020
VL - 16
IS - 3
SN - 1555-2578
AB - Accurate aerodynamic heating prediction is of great significance to current manned space flight and deep space exploration missions. The temperature in
the shock layer surrounding the reentry vehicle can reach up to 10,000 K and
result in remarkable thermochemical nonequilibrium, as well as considerable
radiative heat transfer. In general, high-temperature flow simulations coupled with
thermal radiation require appropriate numerical schemes and physical models. In
this paper, the equations governing hypersonic nonequilibrium flow, based on a
three-temperature model combined with a thermal radiation solving approach,
are used to investigate the radiation effects in the reentry shock layer. An axisymmetric spherical case shows that coupling the flow-field simulation with radiation
has a scarce influence on the convective heating prediction, but has some impact
on the radiative heating calculation. In particular, for the Apollo capsule reentry,
both the absorption coefficient and incident radiation are remarkable inside the
shock layer. The radiative heating maximum reaches nearly 38% of that of the
convective heating making a considerable contribution to the total aerodynamic
heating. These results indicate that in the hypersonic regime, in order to account
for the total heating, it is necessary to simulate the high-temperature thermochemical nonequilibrium flows coupled with thermal radiation.
KW - Reentry; nonequilibrium; aerodynamic heating; thermal radiation
DO - 10.32604/fdmp.2020.09624