高速稀薄非平衡边界层输运分析与气动力热理论预测

欧吉辉; 陈杰

doi:10.7638/kqdlxxb-2026.0076

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高速稀薄非平衡边界层输运分析与气动力热理论预测

研究专栏——稀薄气体动力学理论与高效计算方法Ⅱ | 更新时间：2026-10-14

- 高速稀薄非平衡边界层输运分析与气动力热理论预测
- Analysis of nonlinear transport in hypersonic rarefied nonequilibrium boundary layer and theoretical prediction of surface aerothermodynamics
- 空气动力学学报 2026年44卷第8期页码：103-115
- 作者机构：
  
  天津大学机械工程学院高速空气动力学研究室,天津,300072
- 作者简介：
  
  陈杰*，副研究员，研究方向：稀薄气体动力学. E-mail：jie.chen@tju.edu.cn
- 基金信息：
  
  国家自然科学基金重大研究计划培育项目（92471106）
- DOI：10.7638/kqdlxxb-2026.0076
  中图分类号： O356
- 纸质出版：2026
- 稿件说明：
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欧吉辉, 陈杰. 高速稀薄非平衡边界层输运分析与气动力热理论预测[J]. 空气动力学学报, 2026, 44(8): 103−115.

Ou Jihui, Chen Jie. Analysis of nonlinear transport in hypersonic rarefied nonequilibrium boundary layer and theoretical prediction of surface aerothermodynamics[J]. 2026, 44(8): 103-115.
欧吉辉, 陈杰. 高速稀薄非平衡边界层输运分析与气动力热理论预测[J]. 空气动力学学报, 2026, 44(8): 103−115. DOI： 10.7638/kqdlxxb-2026.0076

Ou Jihui, Chen Jie. Analysis of nonlinear transport in hypersonic rarefied nonequilibrium boundary layer and theoretical prediction of surface aerothermodynamics[J]. 2026, 44(8): 103-115. DOI： 10.7638/kqdlxxb-2026.0076.

摘要

准确快速预测壁面气动力热对飞行器设计至关重要。临近空间飞行器跨越大气层飞行时将受到稀薄气体效应的显著影响，导致传统纳维-斯托克斯（Navier-Stokes

N-S）方程失效，给飞行器表面气动力热的准确高效预测带来挑战，准确描述飞行器近壁边界层的非线性输运特性对于气动力热预测非常关键。对此，本文针对高速稀薄非平衡边界层，基于Grad 13矩方程和广义流体动力学方程进行理论分析，结合剪切流Boltzmann模型方程的正则解和直接模拟蒙特卡罗（direct simulation Monte Carlo

DSMC）模拟结果，研究了边界层内的非平衡机理和非线性输运特性，给出了边界层主导输运关系式和非平衡效应表征参数，发展了壁面局部压力、摩阻和热流的关联预测公式，并在尖平板、钝平板、钝楔、钝锥及圆球绕流等不同外形下与DSMC模拟结果进行了对比验证。结果表明，边界层内应力张量和热流矢量各分量的主导输运关系式均可表达为剪切非平衡参数

和热力梯度非平衡参数

的显式函数；所建立的壁面气动力热关联公式可显著改进传统N-S计算结果，在从连续到早期过渡流区（

～1）与DSMC模拟结果吻合良好。该公式可以仅在连续流N-S解（解析或数值）基础上给出对稀薄过渡流壁面气动力热的近似准确估计，无需求解矩方程或动理论方程，在近空间飞行器壁面气动力热快速预测方面具有很好的应用前景。

Abstract

Accurate and rapid prediction of surface aerothermodynamics is critical for flying vehicle design. Near-space vehicles flying across the atmosphere are significantly affected by rarefied gas effects

which render the co

nventional Navier-Stokes (N-S) equations invalid and pose challenges to the accurate and efficient prediction of surface aerothermodynamics. In particular

the accurate description of nonlinear transport in the near-wall boundary layer is crucial for aerodynamic predictions. To address this

the present study conducted a theoretical analysis of hypersonic rarefied nonequilibrium boundary layers based on the Grad 13 moment equations (G13) and generalized hydrodynamic equations (GHE)

in conjunction with the normal solutions of the Boltzmann model equation for shear flows and the simulation results from the direct simulation Monte Carlo (DSMC) method. The nonequilibrium mechanisms and nonlinear transport characteristics within the boundary layer were investigated

from which the leading transport relations and the parameters characterizing nonequilibrium effects were derived. A set of correlation formulae for local surface pressure

skin friction

and heat flux were developed

and were validated against DSMC simulations for various geometries

including flat plate

blunt plate

blunt wedge

blunt cone

and sphere. The results show that the nonlinear transport functions for each component of stress and heat flux in the boundary layer can be expressed as explicit functions of the shear nonequilibrium parameter

and thermal gradient nonequilibrium parameter

. The established correlation formulae significantly improve the traditional N-S predictions and agree well with DSMC results from the continuum to early transitional regimes (

～1). Notably

these formulae can provide approximate yet accurate estimates of surface aerothermodynamics for the hypersonic transitional flows using only the continuum-based N-S solutions (either analytical or numerical)

without solving moment or kinetic equations

thus showing promising prospects for rapid prediction of surface aerothermodynamics on

near-space vehicles.

关键词

Keywords

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