Radiative equilibrium boundary for DSMC menthod and its application of double-cone configuration

JIN Hao; FANG Ming; LI Langquan; LIU Sha; ZHONG Chengwen

doi:10.7638/kqdlxxb-2020.0128

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Radiative equilibrium boundary for DSMC menthod and its application of double-cone configuration

更新时间：2026-05-28

- Radiative equilibrium boundary for DSMC menthod and its application of double-cone configuration
- Vol. 39, Issue 5, Pages: 75-81(2021)
- 作者机构：
  
  1. 西北工业大学航空学院,西安,710072
  2. 中国空气动力研究与发展中心,绵阳,621000
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2020.0128
  CLC： O414.14
- Published：2021
- 稿件说明：
移动端阅览
金浩, 方明, 李埌全, 等. 壁面辐射平衡DSMC方法及其在双锥构型中应用[J]. 空气动力学学报, 2021, 39(5): 75−81.

JIN Hao, FANG Ming, LI Langquan, et al. Radiative equilibrium boundary for DSMC menthod and its application of double-cone configuration[J]. 2021, 39(5): 75-81.
金浩, 方明, 李埌全, 等. 壁面辐射平衡DSMC方法及其在双锥构型中应用[J]. 空气动力学学报, 2021, 39(5): 75−81. DOI： 10.7638/kqdlxxb-2020.0128

JIN Hao, FANG Ming, LI Langquan, et al. Radiative equilibrium boundary for DSMC menthod and its application of double-cone configuration[J]. 2021, 39(5): 75-81. DOI： 10.7638/kqdlxxb-2020.0128.

摘要

临近空间高超声速飞行器在高空长时间飞行，受气流加热影响，飞行器表面温度显著升高，依赖地面试验和传统DSMC仿真预测的热流值明显高于飞行观测值，导致飞行器防热系统的保守设计。本文发展了一种基于壁面辐射平衡的DSMC边界模型，通过热流值反算辐射平衡壁面温度，并以此温度作为下一个时间步DSMC计算的边界条件，迭代更新至给出壁面温度的收敛值。基于该温度边界条件，开发了适用于轴对称构型的DSMC求解器，并以钝锥构型对计算模型和求解器进行了验证。重点针对激波风洞试验条件下的双锥构型，开展数值模拟研究，结果表明：该构型恒温冷壁条件得到的壁面压力分布和热流与风洞试验结果吻合，两种温度条件下的压力峰值差异约为15.4%，但是整体气动力特性差异仅约为0.33%；相对于冷壁，辐射平衡计算得到的前缘处热流峰值降低约50%，再附点处的热流峰值降低约三分之二；两种条件相结合，可以给出壁面热流的预测范围。

Abstract

For high altitude long endurance hypersonic vehicle

the surface temperature is increased significantly due to aerodynamic heating. The pneumatic heating data obtained by ground wind tunnel tests and traditional DSMC simulation is obviously higher than flight observations

leading to conservative design of thermal protection systems. A wall boundary condition based on radiative equilibrium is studied and developed

in which the wall temperature is inversely calculated by the pneumatic heating flux and the temperature is used as the boundary condition of next time step calculation until it converges. Based on the boundary condition

the DSMC solver for axisymmetric configurations is developed and validated through the blunted cone computation. We focus on the double-cone configuration

and the numerical simulation of double-cone is carried out in condition of the shock wave wind tunnel test. Test cases show that the heat flux and pressure in constant temperature cold wall condition are consistent with those in the ground wind tunnel test. In two temperature boundary conditions

the peak pressure has the difference of 15.4%

but the difference of total aerodynamic coefficient is only 0.33%. Compared with the result in cold wall condition

the peak heat flux at the leading edge is reduced by about 50%

and that at the reattachment point is reduced by 66.67%. According to the results in two conditions

the range of surface heat flux can be given.

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Keywords

references

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