有局部稀薄气体效应的高超声速流动数值模拟

欧吉辉; 赵磊; 陈杰

doi:10.7638/kqdlxxb-2018.0179

欢迎来到能源电力期刊网！

English Version 期刊登录

您当前的位置：

首页 >

文章列表页 >

有局部稀薄气体效应的高超声速流动数值模拟

研究论文 | 更新时间：2026-05-28

- 有局部稀薄气体效应的高超声速流动数值模拟
- Numerical simulation of hypersonic flows with local rarefaction effect
- 空气动力学学报 2019年37卷第2期页码：193-200
- 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：
  
  欧吉辉(1993-), 男, 四川人, 博士研究生, 研究方向:稀薄气体动力学.E-mail:oujihui@tju.edu.cn
  陈杰, Tel:022-27405022, E-mail:jie.chen@tju.edu.cn
- 基金信息：
  
  国家自然科学基金（11802202，11732011）
- DOI：10.7638/kqdlxxb-2018.0179
  中图分类号： V211.3
- 纸质出版：2019
- 稿件说明：
移动端阅览
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

CHEN J, ZHAO L. A criterion for the existence of local rarefaction in a hypersonic flow field and corresponding flow characteristics[J]. Acta Aerodynamica Sinica, 2018, 36(1):4-11. (in Chinese)

ZHOU H, ZHANG H X. New problems of aerodynamics[J]. Sci Sin-Phys Mech Astron, 2015, 45:104709. (in Chinese)

LI Z H, WU Z Y. DSMC simulation on rarefied aerodynamics of Apollo-CM[J]. Acta Aerodynamica Sinica, 1996, 14(2):230-233. (in Chinese)

ZHUANG F G, CUI E J, ZHANG H X. Some development of future spacecrafts and aerodynamics tasks[C]//Proc of First Aerodynamics and Aerothermodynamics. Mianyang: China Aerodynamics Research and Development Center, 2006: 1-12. (in Chinese)

BIRD G A. Molecular gas dynamics and the direct simulation of gas flows[M]. Oxford:Clarendon Press. 1994.

RAULT D F G. Aerodymics of the Shuttle Orbiter at high altitudes[J]. Journal of Spacecraft and Rockets, 1994, 31(6):944-952.

BIRD G A. The DSMC method[M]. CreateSpace Independent Publishing Platform, 2013.

FAN J. Rarefied gas dynamics:Advances and applications[J]. Advances in Mechanics, 2013, 43(2):185-201. (in Chinese)

WU L, WHITE C, SCANLON T C, et al. Deterministic numerical solutions of the Boltzmann equation using the fast spectral method[J]. J Comput Phys, 2013, 250(1):27-52.

NIE X B, DOOLEN G D, CHEN S. Lattice-Boltzmann simulations of fluid flows in MEMS[J]. Journal of Statistical Physics, 2002, 107(1-2):279-289.

HE X, LUO L S. Lattice Boltzmann model for the incompressible Navier-Stokes equation[J]. Journal of Statistical Physics, 1997, 88(3-4):927-944.

LIN C D, LUO K H. MRT discrete Boltzmann method for compressible exothermic reactive flows[J]. Computers Fluids, 2018, 166:176-183.

XU K, HUANG J C. A unified gas-kinetic scheme for continuum and rarefied flows[J]. Journal of Computational Physics, 2010, 229(20):7747-7764.

LI Z H, ZHANG H X. Study on gas kinetic unified algorithm for flows from rarefied transition to continuum[J]. Journal of Comput Phys, 2004, 193(2):708-738.

SCHWARTZENTRUBER T E, SCALABRIN L C, BOYD I D. Hybrid particle-continuum simulations of nonequilibrium hypersonic blunt-body flowfields[J]. Journal of Thermophysics and Heat Transfer, 2008, 22(1):29-37.

XU X, WANG X, ZHANG M, et al. A parallelized hybrid N-S/DSMC-IP approach based on adaptive structured/unstructured overlapping grids for hypersonic transitional flows[J]. Journal of Computational Physics, 2018:S0021-9991(18)30321-8.

LOFTHOUSE A J, SCALABRIN L C, BOYD I D. Velocity slip and temperature jump in hypersonic aerothermodynamics[J]. Journal of thermophysics and heat transfer, 2008, 22(1):38-49.

TITOV E, BURT J, JOSYULA E, et al. Implications of slip boundary conditions on surface properties in hypersonic flows[C]//43rd AIAA Thermophysics Conference. 2012: 3307.

HUANG F, ZHANG L, CHENG X L, et al. Effects of continuum breakdown on aerodynamics of near space vehicle[J]. Acta Aerodynamica Sinica, 2013, 31(5):623-628. (in Chinese)

LOCKERBY D A, REESE J M, GALLIS M A. Capturing the Knudsen layer in continuum-fluid models of nonequilibrium gas flows[J]. AIAA Journal, 2005, 43(6):1391-1393.

GUO Z L, SHI B C, ZHENG C G. An extended Navier-Stokes formulation for gas flows in the Knudsen layer near a wall[J]. EPL (Europhysics Letters), 2007, 80(2):24001.

DONGARI N, ZHANG Y, REESE J M. Modeling of Knudsen layer effects in micro/nanoscale gas flows[J]. Journal of Fluids Engineering, 2011, 133(7):071101.

ZHAO L. Study on instability of stationary crossflow vortices in hypersonic swept blunt plate boundary layers[D]. Tianjin University, 2017. (in Chinese)

DENG X G, ZHANG H X. The extentions of NND schemes and application to viscous flow calculations[J]. Acta Aerodynamica Sinica, 1994, 12(2):121-129. (in Chinese)

JIANG G S, SHU C W. Efficient implementation of weighted ENO schemes[J]. Journal of Computational Physics, 1996, 126(1):202-228.

浏览量

下载量

CSCD

文章被引用时，请邮件提醒。

提交

工具集

关联资源

凹腔对高超声速边界层稳定性的影响

考虑化学非平衡效应的高温湍流边界层统计特性分析

基于修正N-S方程本构关系的气体动理论耦合方法

可压缩湍流边界层壁面函数方法综述

高超声速流动稳定性及转捩工程应用若干研究进展