高温气体效应下流动转捩及超声速模态的线性演化

赵洲源; 陈贤亮; 王亮; 符松

doi:10.7638/kqdlxxb-2023.0168

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高温气体效应下流动转捩及超声速模态的线性演化

研究论文 | 更新时间：2026-05-28

- 高温气体效应下流动转捩及超声速模态的线性演化
- Evolution and development of flow transition and supersonic modes under high-temperature gas effects
- 空气动力学学报 2024年42卷第4期页码：75-83
- 作者机构：
  
  清华大学航天航空学院,北京,100084
- 作者简介：
  
  赵洲源（1994—），河北定州人，助理工程师，研究方向：流动稳定性与转捩. E-mail：zhao-zy21@mails.tsinghua.edu.cn
  王亮，副教授，研究方向：流动稳定性与转捩. E-mail：wangliang12@tsinghua.edu.cn
- 基金信息：
  
  国家重点研发计划（2019YFA0405200）;国家自然科学基金（12072173）;国家重大项目（GJXM92579）;国家科技重大专项（2017-II-0004-0016）
- DOI：10.7638/kqdlxxb-2023.0168
  中图分类号： O357.4;V211
- 纸质出版：2024
- 稿件说明：
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赵洲源, 陈贤亮, 王亮, 等. 高温气体效应下流动转捩及超声速模态的线性演化[J]. 空气动力学学报, 2024, 42(4): 75−83.

ZHAO Zhouyuan, CHEN Xianliang, WANG Liang, et al. Evolution and development of flow transition and supersonic modes under high-temperature gas effects[J]. 2024, 42(4): 75-83.
赵洲源, 陈贤亮, 王亮, 等. 高温气体效应下流动转捩及超声速模态的线性演化[J]. 空气动力学学报, 2024, 42(4): 75−83. DOI： 10.7638/kqdlxxb-2023.0168

ZHAO Zhouyuan, CHEN Xianliang, WANG Liang, et al. Evolution and development of flow transition and supersonic modes under high-temperature gas effects[J]. 2024, 42(4): 75-83. DOI： 10.7638/kqdlxxb-2023.0168.

摘要

对转捩的精确预测已成为飞行器气动设计的关键环节，然而转捩问题相当复杂并对诸多因素敏感。在超高速高温流动中，转捩和高温气体效应深度耦合，特别是在激波、壁面附近和分离区等速度梯度很大的区域，热化学过程对流动转捩的影响不容忽视。在自然转捩过程中，不同的扰动形式在流场中的发展各不相同，进而对转捩进程造成的影响也不同。同时，超高速边界层内存在多种模态，其中第二模态下游区域出现的不稳定的超声速模态值得关注和研究。本文通过求解线性抛物化稳定性方程（LPSE）研究了高温气体效应下流动转捩及超声速模态的演化发展。结果表明：与量热完全气体流动相比，考虑热化学过程的流动使得温度边界层更薄，类似“冷壁”的作用，进而使得扰动的超声速模态更容易出现；分子振动平衡使得流动的温度边界层进一步变薄，即使在较高的壁温条件下，扰动的超声速模态依然存在；同时，低频扰动下的超声速模态更不稳定，流动易出现转捩。此外，马赫数20、半顶角6°的尖楔绕流算例中，“冷壁”和低频扰动下的超声速模态在特定扰动波角下会出现新的变化。

Abstract

In the design process of hypersonic vehicles

the precise prediction of transition has become a crucial challenge in aerodynamic design. However

the transition problem is quite complex and sensitive to various factors. In high-temperature hypersonic flows

transition and high-temperature gas effects are deeply coupled. The influence of thermochemical processes on flow transition cannot be ignored

especially in regions with significant velocity gradients

such as near shock waves

near-wall

and separation regions. In natural transition processes

different forms of perturbations develop differently in the flow field

subsequently affecting the transition process. Additionally

there are multiple modes in the hypersonic boundary layer

with particular attention and research warranted for the unstable supersonic modes that occur downstream in the second mode.This article investigates evolution and development of flow transition and supersonic modes under high-temperature gas effects by solving the linear PSE (Parabolized Stability Equation). Compared to the flow of calorically perfect gas

considering thermochemical processes in the flow results in a thinner temperature boundary layer

similar to a "cool wall" effect

making perturbations in supersonic modes more likely to occur. Molecular vibrational equilibrium further reduces the thickness of the temperature boundary layer in the flow

allowing the existence of perturbations in supersonic modes even under high wall temperature conditions. Additionally

under low-frequency perturbations

supersonic modes are more unstable

making the flow more prone to transition. Furthermore

in the case of flow around a sharp wedge under a Mach number of 20 and a half-angle of 6 degrees with “cold wall” and low-frequency perturbations

new variations in supersonic modes occur at specific perturbation angles.

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references

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