北京航空航天大学学报 ›› 2018, Vol. 44 ›› Issue (5): 1102-1109.doi: 10.13700/j.bh.1001-5965.2017.0303

• 论文 • 上一篇    下一篇

来流导致的高超声速气动热不确定度量化分析

张伟, 王小永, 于剑, 阎超   

  1. 北京航空航天大学 航空科学与工程学院, 北京 100083
  • 收稿日期:2017-05-12 出版日期:2018-05-20 发布日期:2018-05-29
  • 通讯作者: 阎超 E-mail:yanchao@buaa.edu.cn
  • 作者简介:张伟,男,硕士研究生。主要研究方向:计算流体力学及飞行器设计;阎超,男,博士,教授,博士生导师。主要研究方向:计算流体力学。

Uncertainty quantification analysis in hypersonic aerothermodynamics due to freestream

ZHANG Wei, WANG Xiaoyong, YU Jian, YAN Chao   

  1. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
  • Received:2017-05-12 Online:2018-05-20 Published:2018-05-29

摘要: 通常的CFD计算都是确定性的,然而复杂工程数值模拟中必然存在误差与不确定度,分析与辨识其不确定度来源,对不确定度进行量化分析,对数值模拟可信度评估有重要意义。在高超声速飞行器气动热计算中,为获得更加可靠的气动热数据和鉴定影响气动热预测的关键因素,对返回舱开展了气动热不确定度量化分析和敏感性分析。首先选取来流速度、来流温度、壁面温度和来流密度4个不确定性输入变量,并且假定来流速度变化范围为±120 m/s(±2%),来流温度、壁面温度和来流密度变化范围为±10%。然后采用拉丁超立方抽样法生成样本,再通过热化学非平衡数值模拟方法进行气动热计算,最后分别运用基于非嵌入式多项式混沌(NIPC)的方法和基于Sobol指数的方法开展不确定度量化和敏感性分析。结果表明,在给定的输入变量不确定度的条件下,壁面热流不确定度不小于15.9%,在驻点和肩部存在峰值分别约为19.8%(0.087 MW/m2)和17.3%(0.076 MW/m2);相比而言,在给定变化范围内壁面热流对来流密度和来流速度更为敏感,来流温度和壁面温度对热流变化不产生明显影响。

关键词: 气动热, 热化学非平衡, 多项式混沌(PC), 不确定度量化, 敏感性分析

Abstract: The CFD calculation is usually deterministic. However, errors and uncertainties always exist in the numerical simulation of complex engineering. Analysis and identification of source of uncertainty, and quantification of uncertainty play important roles in assessing the credibility of simulation results. Uncertainties are generally ubiquitous in highly complex aerospace systems. To obtain more reliable aerothermodynamics prediction, the uncertainty quantification and sensitivity analysis were carried out for the returning capsule hypersonic reentry flight. First, four uncertainty input variables (freestream velocity, freestream temperature, wall temperature and freestream density) were selected, whose variation ranges are ±120 m/s (±2%), ±10%, ±10% and ±10% respectively. And the samples were generated by Latin hypercube Design. Then, the thermochemical non-equilibrium numerical simulation method was used to calculate the aerodynamic heat. Finally, methods based on non-intrusive polynomial chaos(NIPC) and Sobol index were applied to uncertainty quantification and sensitivity analysis. The results show that the wall heat flux is not less than 15.9% under the given condition of uncertainty input variable uncertainty, and the peak value of the stagnation and shoulder are about 19.8% (0.087 MW/m2) and 17.3% (0.076 MW/m2) respectively. The uncertainty of heat flux is more sensitive to freestream density and velocity, and meanwhile freestream temperature and wall temperature variations almost have no impact on heat flux.

Key words: aerothermodynamics, thermochemical non-equilibrium, polynomial chaos (PC), uncertainty quantification, sensitivity analysis

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