高超声速飞行器表面温度分布与气动热耦合数值研究

doi:10.7527/S1000-6893.2014.0241

Abstract

Abstract:

In order to predict precisely aeroheating and effects of high-temperature non-equilibrium gas during design the thermal protection system of hypersonic vehicles, the simulation methods of coupled surface temperature and heat transfer rate are developed based on the Navier-Stokes equations of non-equilibrium flow fields, the energy conservation equation at the surface with radiation, catalytic action and ablation, and the unsteady heat conduction equations of heat-shield, and the computational code AEROPH_Flow is perfected ,which are developed by us for numerically simulating the flow over hypersonic vehicles and predicting the aero-physical characteristics . The numerical simulation results are presented, including a semi-sphere geometries at the altitude of 65 km with the free stream velocity of 8 km/s and 10 km/s, a sphere-cone geometries at the altitude of 50 km with 8 km/s, and the polycrystalline graphite is selected as ablative material on the surface. The distributions of surface temperature and heat transfer rate are obtained and the analysis is done for the influence of the surface temperature distribution on heat transfer rate. The results show that the surface temperature distribution has a more important influence on the computational results of heat transfer rate, the factors considered in the high-precision prediction of aero-thermal environment are not only thermo-chemical non-equilibrium effect and surface catalytic effect, but also the surface temperature distributions, so the best method for high-precision prediction of aero-thermal environment is the coupling of surface temperature and heat transfer rate, and it is essential to develop perfect physical models, solving methods and numerical simulation codes of coupled non-equilibrium flow field, surface catalytic action and ablation, and heat conduction of heat-shield for the high-precision prediction of aero-thermal environment of hypersonic vehicles under the real flight condition.

Key words: hypersonic vehicle, thermo-chemical non-equilibrium effect, surface temperature distribution, aerodynamic heat environment, numerical simulation

CLC Number:

V434⁺.11

DONG Weizhong, GAO Tiesuo, DING Mingsong, JIANG Tao, LIU Qingzong. Numerical study of coupled surface temperature distribution and aerodynamic heat for hypersonic vehicles[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(1): 311-324.

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Numerical study of coupled surface temperature distribution and aerodynamic heat for hypersonic vehicles

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