### 高超声速飞行器表面温度分布与气动热耦合数值研究

1. 中国空气动力研究与发展中心, 绵阳 621000
• 收稿日期:2014-07-04 修回日期:2014-10-13 出版日期:2015-01-15 发布日期:2015-01-24
• 通讯作者: 董维中,Tel.: 0816-2463298 E-mail: dongwz1966@163.com E-mail:dongwz1966@163.com
• 作者简介:董维中 男, 博士, 研究员, 博士生导师。主要研究方向: 气动物理学和计算高温气体动力学。 Tel: 0816-2463298 E-mail: dongwz1966@163.com
• 基金资助:

国家自然科学基金 (91216204)

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

DONG Weizhong, GAO Tiesuo, DING Mingsong, JIANG Tao, LIU Qingzong

1. China Aerodynamics Research and Development Center, Mianyang 621000, China
• Received:2014-07-04 Revised:2014-10-13 Online:2015-01-15 Published:2015-01-24
• Supported by:

National Natural Science Foundation of China (91216204)

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.