高速斜板液膜冷却的数值模拟研究

邵芳琪; 韩桂来; 杨旸; 周芳; 王大高; 李宗贤; 钱丽娟

doi:10.7638/kqdlxxb-2024.0203

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高速斜板液膜冷却的数值模拟研究

研究论文 | 更新时间：2026-05-28

- 高速斜板液膜冷却的数值模拟研究
- Numerical simulation of liquid film cooling on hypersonic oblique plate
- 空气动力学学报 2026年44卷第2期页码：137-147
- 作者机构：
  
  1. 中国计量大学机电工程学院,杭州,310018
  2. 中国科学院力学研究所，高温气体动力学国家重点实验室,北京,100190
  3. 中国科学院大学工程科学学院,北京,100190
  4. 中国运载火箭技术研究院,北京,100076
- 作者简介：
  
  邵芳琪（2001—），女，河南三门峡人，硕士研究生，研究方向：高速空气动力学. E-mail：SHAOfangqi888@163.com
  韩桂来*（1984—），男，江苏东台人，研究员，研究方向：高速空气动力学、激波与爆轰物理、高速飞行器设计、计算流体力学、实验流体力学等. E-mail：hanguilai@imech.ac.cn
- 基金信息：
  
  国家重点研发计划项目（2022YFB3207000）;国家自然科学基金（12132017）;中国科学院青年交叉团队项目（JCTD-2022-02）;中国科学院青年创新促进会项目（2020019）
- DOI：10.7638/kqdlxxb-2024.0203
  中图分类号： V221.3;TK124;O359.1
- 纸质出版：2026
- 稿件说明：
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邵芳琪, 韩桂来, 杨旸, 等. 高速斜板液膜冷却的数值模拟研究[J]. 空气动力学学报, 2026, 44(2): 137−147.

Shao Fangqi, Han Guilai, Yang Yang, et al. Numerical simulation of liquid film cooling on hypersonic oblique plate[J]. 2026, 44(2): 137-147.
邵芳琪, 韩桂来, 杨旸, 等. 高速斜板液膜冷却的数值模拟研究[J]. 空气动力学学报, 2026, 44(2): 137−147. DOI： 10.7638/kqdlxxb-2024.0203

Shao Fangqi, Han Guilai, Yang Yang, et al. Numerical simulation of liquid film cooling on hypersonic oblique plate[J]. 2026, 44(2): 137-147. DOI： 10.7638/kqdlxxb-2024.0203.

摘要

临近空间飞行器面临严重的气动加热问题，液膜因具有高效的冷却能力被认为是有前景的热防护途径之一。本文针对马赫数5条件下的斜板液膜冷却过程开展数值模拟，采用二阶精度耦合隐式算法求解Navier-Stokes方程，通过流体体积法和网格自适应加密技术捕捉两相流动界面及相间的相互作用，并引入蒸发模型模拟液体蒸发吸热过程。分析了高速斜板表面液膜铺展、演化过程中的流场典型结构，讨论了冷却工质的质量流量、表面张力、黏度系数和斜板倾角对液膜冷却性能的影响机理和规律。结果表明：引入液相冷却工质使斜板壁面热流降低了40%～87%，对壁面起到了很好的冷却效果；壁面热流系数随冷却工质质量流量、表面张力、黏度系数的增大而增大，随斜板倾角的增大而减小。本文研究揭示了气动热与冷却液膜之间的作用机制，为解决高速飞行器热防护系统的热管理问题提供了新的思考。

Abstract

Near-space vehicles encounter significant aerodynamic heating challenges. Liquid films are considered a promising thermal protection approach due to their efficient cooling capabilities. This study numerically investigated the liquid film cooling process on an oblique plate at Mach 5. A second-order accurate coupled implicit algorithm was employed to solve the Navier-Stokes equations. The volume of fluid (VOF) method coupled with adaptive mesh refinement was utilized to capture the two-phase flow interface and interphase interactions. An evaporation model was introduced to simulate the endothermic process during liquid evaporation. The characteristic flow field structures during the spreading and evolution of the liquid film on the hypersonic oblique plate surface were analyzed. Furthermore

the effects and mechanisms of coolant mass flow rate

surface tension

viscosity coefficient

and plate inclination angle on liquid film cooling performance were discussed. The introduction of liquid-phase coolant reduced the wall heat flux on the oblique plate by approximately 40%—87%

demonstrating significant cooling performance. The wall heat flux reduction coefficient increases with increasing coolant mass flow rate

surface tension

viscosity coefficient

and decreasing plate inclination angle. This study reveals the interaction mechanism between aerodynamic heating and the cooling liquid film

providing new insights for addressing thermal management challenges in hypersonic vehicle thermal protection systems.

关键词

Keywords

references

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