A multi-field coupled computing platform using multi-zone iteration is developed to solve conjugate heat transfer problems. Based on the element features of the finite element method (FEM) and finite volume method (FVM), a local conservative remapping method is presented for thermal flux and aerodynamic load interpolation. Shared memory is employed for faster data exchange for the general FEMs/computational fluid dynamics (CFD) software. The problems of conjugate heat transfer for a cooled converging-diverging nozzle and a cylindrical leading edge in hypersonic flow are studied. Effects of mesh density, nonlinear material properties and radiation are considered during the computation,and the results show good agreement with the existing experimental data. The relationships are investigated between the stagnation temperature, cooling power and the thickness of the nose thermal protection structure (TPS) of a quasi-X-34 hypersonic vehicle under hypersonic cruise conditions. The results indicate that the thickness variations exhibit no significant influence on stagnation temperature, while the cooling power drops sharply as the thickness increases. Furthermore, the nonlinear material emission pro-perties have significant influence on the analysis results.
ZHANG Bing, HAN Jinglong
. Multi-field Coupled Computing Platform and Thermal Transfer of Hypersonic Thermal Protection Structures[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2011
, 32(3)
: 400
-409
.
DOI: CNKI:11-1929/V.20101229.1626.001
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