关键参数对高速圆锥边界层来流慢声波扰动感受性的影响规律

陈奕宁; 李晨辉; 万兵兵; 涂国华; 陈坚强

doi:10.7638/kqdlxxb-2024.0182

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关键参数对高速圆锥边界层来流慢声波扰动感受性的影响规律

研究论文 | 更新时间：2026-05-28

- 关键参数对高速圆锥边界层来流慢声波扰动感受性的影响规律
- Effect of key parameters on receptivity of high-speed cone boundary layer to freestream slow acoustic waves
- 空气动力学学报 2026年44卷第1期页码：30-38
- 作者机构：
  
  1. 空天飞行空气动力科学与技术全国重点实验室,绵阳,621000
  2. 北京航空航天大学航空科学与工程学院,北京,100191
- 作者简介：
  
  陈奕宁（2000—），男，河北邯郸，硕士研究生，研究方向：高速边界层转捩. E-mail：1064202204@qq.com
  万兵兵*，副研究员，研究方向：高速边界层转捩. E-mail：wanbing@tju.edu.cn
  陈坚强*，研究员，研究方向：复杂流动数值模拟与机理. E-mail：chenjq@cardc.cn
- 基金信息：
  
  某试验鉴定技术研究项目（2022G02000250007）
- DOI：10.7638/kqdlxxb-2024.0182
  中图分类号： V211.1
- 纸质出版：2026
- 稿件说明：
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陈奕宁, 李晨辉, 万兵兵, 等. 关键参数对高速圆锥边界层来流慢声波扰动感受性的影响规律[J]. 空气动力学学报, 2026, 44(1): 30−38.

Chen Yining, Li Chenhui, Wan Bingbing, et al. Effect of key parameters on receptivity of high-speed cone boundary layer to freestream slow acoustic waves[J]. 2026, 44(1): 30-38.
陈奕宁, 李晨辉, 万兵兵, 等. 关键参数对高速圆锥边界层来流慢声波扰动感受性的影响规律[J]. 空气动力学学报, 2026, 44(1): 30−38. DOI： 10.7638/kqdlxxb-2024.0182

Chen Yining, Li Chenhui, Wan Bingbing, et al. Effect of key parameters on receptivity of high-speed cone boundary layer to freestream slow acoustic waves[J]. 2026, 44(1): 30-38. DOI： 10.7638/kqdlxxb-2024.0182.

摘要

边界层层流-湍流转捩预测是空气动力学与飞行器设计的研究热点。基于线性稳定性理论的e

方法虽已应用于工程实践，但通常忽略了外界扰动激发边界层不稳定波的过程，理论上仍有不足。目前针对多参数影响的感受性规律尚缺乏系统研究。本文以高速圆锥边界层为研究对象，采用感受性数值模拟方法和稳定性理论分析方法，研究头部钝度、壁温、单位雷诺数、频率等关键参数对来流慢声波感受性的影响规律。研究发现，感受性系数整体上随钝度增加而减小，随壁温降低而增大，而受单位雷诺数变化影响不大。针对不同频率的来流扰动，在绝热壁或热壁条件下激发的边界层不稳定模态包括第一模态和第二模态，其中第一模态感受性系数比第二模态高1～2个量级以上。此外，在激发第一模态的频率范围内，感受性系数随频率增加而减小；在激发第二模态的频率范围内，感受性系数随频率的变化规律主要受钝度影响：小钝度时先减小后增大，中等钝度时单调递减，较大钝度时先增大后减小。

Abstract

Predicting the boundary-layer transition process is a hot research issue in aerodynamics as well as an engineering demand for aircraft design. The e

method based on linear stability theory is widely regarded as the most scientific method for transition prediction

which has been applied in engineering practices. However

this method has theoretical shortcomings as it traditionally ignores the receptivity of the boundary layer to external disturbances

i.e.

the process of exciting boundary-layer unstable waves by external dist

urbances. The influence factors of receptivity are numerous

but at present

their influence laws are relatively less studied and not systematically understood yet. In this study

the high-speed cone boundary layer is taken as the object to investigate the influence of key parameters such as nose bluntness

wall temperature

unit Reynolds number

and frequency on the receptivity of boundary layers to freestream slow acoustic waves. The used methods include numerical simulations of receptivity and linear stability theory. It is found that

overall

the receptivity coefficient decreases as the nose bluntness increases

and increases as the wall temperature decreases

but is almost unaffected by the unit Reynolds number. For freestream disturbances with different frequencies

the unstable mode excited in the boundary layer under adiabatic or heated wall temperature conditions include the first and second modes

among which the receptivity coefficient of the first mode is 1-2 orders of magnitude higher than that of the second mode. In addition

the receptivity coefficient decreases with increasing frequency in the first-mode excited frequency range

while it is mainly affected by the nose bluntness in the second-mode excited frequency range. The receptivity coefficient decreases first then increases with the frequency for small bluntness

decreases monotonically with the frequency for medium bluntness

and increases first then decreases for large bluntness.

关键词

Keywords

references

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