Numerical simulation of hypersonic flows with local rarefaction effect

OU Jihui; ZHAO Lei; CHEN Jie

doi:10.7638/kqdlxxb-2018.0179

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Numerical simulation of hypersonic flows with local rarefaction effect

更新时间：2026-05-28

- Numerical simulation of hypersonic flows with local rarefaction effect
- Vol. 37, Issue 2, Pages: 193-200(2019)
- 作者机构：
  
  1. 天津大学机械工程学院高速空气动力学研究室, 天津市现代工程力学重点实验室,天津,300350
  2. 中国空气动力研究与发展中心超高速空气动力研究所,绵阳,621000
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2018.0179
  CLC： V211.3
- Published：2019
- 稿件说明：
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欧吉辉, 赵磊, 陈杰. 有局部稀薄气体效应的高超声速流动数值模拟[J]. 空气动力学学报, 2019, 37(2): 193-200.

OU Jihui, ZHAO Lei, CHEN Jie. Numerical simulation of hypersonic flows with local rarefaction effect[J]. 2019, 37(2): 193-200.
欧吉辉, 赵磊, 陈杰. 有局部稀薄气体效应的高超声速流动数值模拟[J]. 空气动力学学报, 2019, 37(2): 193-200. DOI： 10.7638/kqdlxxb-2018.0179.

OU Jihui, ZHAO Lei, CHEN Jie. Numerical simulation of hypersonic flows with local rarefaction effect[J]. 2019, 37(2): 193-200. DOI： 10.7638/kqdlxxb-2018.0179.

摘要

近空间高超声速飞行器当飞行高度和速度足够高时，其流场计算可能要考虑稀薄气体效应，传统的计算流体力学（CFD）方法预测的阻力和升阻比将不够准确。而现有的模拟稀薄气体流动的计算方法由于其计算量巨大，难以在工程实际中应用。因此需要发展能用于近空间高超声速飞行器流场的可行、可靠的计算方法。陈杰和赵磊在文献[1

]

中针对边界层中既有强剪切而气体分子自由程又相对较大的情况进行分析，提出了刻画此类局部稀薄效应的无量纲参数

，并提出了在传统CFD中通过采用依赖于

参数的等效黏性系数考虑局部稀薄效应对阻力计算影响的研究思路。因此，本文尝试将此等效黏性系数纳入CFD模型中，以在70 km高空，以马赫数15飞行的小迎角钝平板为例，来检验计算方法是否合理可行。结果表明：和传统的CFD方法所得结果相比，新模型计算的阻力减小，升阻比增加，其改进的方向与现有飞行试验结果定性相符，且所增加的计算时间非常有限，可方便地应用于现有的计算空气动力学中。

Abstract

For vehicles at high Mach number and high altitude in near space

CFD may not be able to provide accurate aerodynamic coefficients of the vehicles

for example

the drag force and the lift to drag ratio. The cause is now acknowledged as the rarefaction effect of the air that has not been taken into consideration in conventional CFD. The current numerical methods for rarefied gas flow are hard to be used in practice due to their enormous computation costs. An accurate and efficient numerical method is necessary. A rarefaction parameter

which characterizes the effect induced by large mean

free path and high shear strengths

was proposed in reference[1

]

published in

Acta Aerodynamica Sinica

in 2018 by Chen Jie and Zhao Lei. Moreover

the relationship between effective viscosity and

was also proposed for the consideration of local rarefaction effect. In the present paper

this effective viscosity model is embed in the CFD to simulate a hypersonic flow over a blunt plate at Mach number 15. The results show that the drag calculated by the new model decreases and the lift-drag ratio increases

compared with that obtained by the conventional CFD method. This belaviour is qualitatively consistent with the existing flight test result. In addition

the computational cost is not be appreciably increased.

关键词

Keywords

references

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