高超声速边界层转捩预测中的关键科学问题——感受性、扰动演化及转捩判据研究进展

苏彩虹

doi:10.7638/kqdlxxb-2020.0056

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高超声速边界层转捩预测中的关键科学问题——感受性、扰动演化及转捩判据研究进展

专栏——中国流动稳定性和转捩研究40年 | 更新时间：2026-05-28

- 高超声速边界层转捩预测中的关键科学问题——感受性、扰动演化及转捩判据研究进展
- Progress in key scientific problems of hypersonic boundary-layer transition prediction: receptivity, evolution of disturbances and transition criterion
- 空气动力学学报 2020年38卷第2期页码：355-367
- 作者机构：
  
  天津大学机械学院高速空气动力学研究室,天津,300072
- 作者简介：
  
  苏彩虹*(1979-), 女, 内蒙古包头人, 教授, 研究方向:流动稳定性和转捩.E-mail:su_ch@tju.edu.cn
- 基金信息：
  
  国家自然科学基金（11872270，11472188，91952202）
- DOI：10.7638/kqdlxxb-2020.0056
  中图分类号： O357.4
- 纸质出版：2020
- 稿件说明：
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苏彩虹. 高超声速边界层转捩预测中的关键科学问题——感受性、扰动演化及转捩判据研究进展[J]. 空气动力学学报, 2020, 38(2): 355-367.

SU Caihong. Progress in key scientific problems of hypersonic boundary-layer transition prediction: receptivity, evolution of disturbances and transition criterion[J]. 2020, 38(2): 355-367.
苏彩虹. 高超声速边界层转捩预测中的关键科学问题——感受性、扰动演化及转捩判据研究进展[J]. 空气动力学学报, 2020, 38(2): 355-367. DOI： 10.7638/kqdlxxb-2020.0056.

SU Caihong. Progress in key scientific problems of hypersonic boundary-layer transition prediction: receptivity, evolution of disturbances and transition criterion[J]. 2020, 38(2): 355-367. DOI： 10.7638/kqdlxxb-2020.0056.

摘要

随着临近空间高超声速飞行技术的发展，预测高超声速边界层转捩位置的需求变得越来越迫切。由于高超声速实验很难做，不可能做得很多，因此像低速飞行器那样的半经验预测方法恐怕很难可靠地实现。为此，需要理解转捩所包含的关键物理过程，在此基础上，发展基于物理机理的转捩预测方法。目前，对于高超声速边界层，转捩预测的不确定性主要来自于转捩过程的一头一尾，即感受性和转捩判据。本文将分别介绍这两方面的最新研究进展和尚存在的问题，特别是有关圆锥边界层具体的感受路径和横流转捩的机理。之后，讨论了在边界层扰动演化方面的问题，包括e

方法在三维边界层中的积分策略，及在高超声速边界层中遇到的第一模态到第二模态的模态转换问题。最后，总结了在完善转捩预测方法上面临的问题和挑战。

Abstract

With the development of hypersonic flight technology in the near space

accurate prediction of the transition location of hypersonic boundary layers is highly desired. Due to the difficulty of implementing hypersonic experiments

there is no enough experimental data to realize a semi-empirical method of transition prediction for high-speed flight vehicles as reliably as their low-speed counterparts. For that purpose

the physical process of transition needs to be understood more thoroughly

and based on which

a reasonable transition prediction method can be establishe

d. So far

for hypersonic boundary layers

the main uncertainties of transition prediction come from the first stage and the last stage of the transition respectively

i.e. the receptivity and the criterion of transition. This paper presents the recent progress and the problems remained in these two aspects

including the specific path in receptivity of a blunt cone boundary layer and the physical mechanism involved in transition induced by cross flow. For the stage of evolutions of disturbances

the integral strategy in applying e

method to the three-dimensional boundary layer

and the intermodal exchange between the first mode and second mode encountered in hypersonic boundary layers are discussed. In conclusion

the problems and challenges are summarized for the improvement of transition prediction method based on linear stability theory.

关键词

Keywords

references

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