辐射平衡壁温下有限催化模型数值模拟

Numerical Simulation of Finite Catalysis Model at the Balanced Radiation Wall

文章发展了高超声速飞行器辐射平衡壁温下有限催化的数值方法,将数值模拟结果与基于返回舱外形的风洞实验数据进行了对比,并进一步针对典型高超声速飞行器钝双锥研究了辐射平衡壁温下有限催化对气动热环境的影响规律.针对返回舱外形的数值实验表明,完全催化与完全非催化边界条件下壁面热流密度均与风洞实验结果偏差较大,而采用合适的有限催化模型获得的壁面热流密度与风洞实验结果符合良好.针对典型高超声速飞行器钝双锥的研究表明,在辐射平衡温度边界条件下驻点附近氧原子的催化复合系数约为0.17,氮原子的催化复合系数约为0.026,大面积区则分别降为0.0053和0.01.在驻点热流密度方面,完全催化的壁面热流峰值比有限催化高约21%,而完全非催化的壁面热流峰值比有限催化低约29%.

In this paper,the numerical method of finite catalysis at the balanced radiation wall of the hypersonic vehicle was developed.The numerical simulation results were compared with the wind tunnel experimental data of the re-entry capsule,and the influence of finite catalysis under balanced radiation wall on the aerodynamic thermal environment was further studied for a typical hypersonic vehicle with a blunt bi-cone.Numerical experiments on the shape of the re-entry capsule show that the heat fluxes under the boundary conditions of full catalysis and non-catalysis deviate greatly from the wind tunnel test results,and the heat flux obtained using the finite catalysis model is in good agreement with the wind tunnel test results.Studies on a typical hypersonic vehicle with a blunt bi-cone show that under the balanced radiation wall,the catalytic recombination coefficient of oxygen atoms near the stagnation point is about 0.17,that of nitrogen atoms is about 0.026,and that in the large area is reduced to 0.0053 and 0.01,respectively.In terms of the heat flux at the stagnation point,the peak heat flux of the full catalyzed wall is about 21%higher than that of the finite catalysis,and the peak heat flux of the non-catalyzed wall is about 29%lower than that of the finite catalysis.