Effect of key parameters on receptivity of high-speed cone boundary layer to freestream slow acoustic waves

Chen Yining; Li Chenhui; Wan Bingbing; Tu Guohua; Chen Jianqiang

doi:10.7638/kqdlxxb-2024.0182

English Version Journal Login

您当前的位置：

首页 >

文章列表页 >

Effect of key parameters on receptivity of high-speed cone boundary layer to freestream slow acoustic waves

更新时间：2026-05-28

- Effect of key parameters on receptivity of high-speed cone boundary layer to freestream slow acoustic waves
- Vol. 44, Issue 1, Pages: 30-38(2026)
- 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：
- 基金信息：
- DOI：10.7638/kqdlxxb-2024.0182
  CLC： V211.1
- Published：2026
- 稿件说明：
移动端阅览
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

Chen Jianqiang, Tu Guohua, Zhang Yifeng, et al. Hypersnonic boundary layer transition: what we know, where shall we go[J]. Acta Aerodynamica Sinica, 2017, 35(3): 311−337(in Chinese). doi: 10.7638/kqdlxxb-2017.0030

An Fuxing, Li Lei, Su Wei, et al. Key issues in hypersonic vehicle aerodynamic design[J]. Scientia Sinica (Physica, Mechanica and Astronomica), 2021, 51(10): 6−25(in Chinese).

Luo Jisheng. Transition and prediction for hypersonic boundary layers[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(1): 357−372(in Chinese).

Zhou Heng, Zhang Hanxin. Two problems in the transition and turbulence for near space hypersonic flying vehicles[J]. Acta Aerodynamica Sinica, 2017, 35(2): 151−155(in Chinese). doi: 10.7638/kqdlxxb-2017.0016

Smith A M O. Transition, pressure gradient and stability theory: ES26388[R]. Douglas Aircraft Co., 1956.

Van Ingen J L. A suggested semi-empirical method for the calculation of the boundary layer transition region [R]. Delft University of Technology, 1956.

Mack L M. Transition prediction and linear stability theory: N78-14316 05-34[R]. AGARD, 1977.

Crouch J D, Kosorygin V S, Ng L L. Modeling the effects of steps on boundary-layer transition[C]//6th IUTAM Symposium on Laminar-Turbulent Transition, 2006. doi: 10.1007/1-4020-4159-4_4

Zhong X L, Wang X W. Direct numerical simulation on the receptivity, instability, and transition of hypersonic boundary layers[J]. Annual Review of Fluid Mechanics, 2012, 44: 527−561. doi: 10.1146/annurev-fluid-120710-101208

Fedorov A V, Khokhlov A P. Excitation of unstable modes in a supersonic boundary layer by acoustic waves[J]. Fluid Dynamics, 1991, 26(4): 531−537. doi: 10.1007/BF01050314

Fedorov A V, Khokhlov A P. Excitation and evolution of unstable disturbances in supersonic boundary layer[C]//Proceedings of the ASME Fluids Engineering Conference. Vancouver: ASME Fluids Engineering Division, 1993, 151: 1−13.

Ma Yanbao, Zhong Xiaolin. Receptivity of a supersonic boundary layer over a flat plate. Part 1. Wave structures and interactions[J]. Journal of Fluid Mechanics, 2003, 488: 31−78. doi: 10.1017/S0022112003004786

Ma Yanbao, Zhong Xiaolin. Receptivity of a supersonic boundary layer over a flat plate. Part 2. Receptivity to free-stream sound[J]. Journal of Fluid Mechanics, 2003, 488: 79−122. doi: 10.1017/S0022112003004798

Malik M, Balakumar P. Receptivity of supersonic boundary layers to acoustic disturbances[C]//Proc of the 35th AIAA Fluid Dynamics Conference and Exhibit, Toronto, Ontario, Canada. Reston, Virginia: AIAA, 2005: 5027. doi: 10.2514/6.2005-5027

He S, Zhong Xiaolin. Hypersonic boundary-layer receptivity over a blunt cone to freestream pulse disturbances[J]. AIAA Journal, 2021, 59(9): 3546−3565. doi: 10.2514/1.J059697

Kara K, Balakumar P, Kandil O A. Effects of nose bluntness on hypersonic boundary-layer receptivity and stability over cones[J]. AIAA Journal, 2011, 49(12): 2593−2606. doi: 10.2514/1.j050032

Kara K, Balakumar P, Kandil O. Receptivity of hypersonic boundary layers due to acoustic disturbances over blunt cone[C]//Proc of the 45th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada. Reston, Virginia: AIAA, 2007: 945. doi: 10.2514/6.2007-945

Kara K, Balakumar P, Kandil O. Effects of wall cooling on hypersonic boundary layer receptivity over a cone[C]//Proc of the 38th Fluid Dynamics Conference and Exhibit, Seattle, Washington. Reston, Virginia: AIAA, 2008: 3734. doi: 10.2514/6.2008-3734

Wan Bingbing, Luo Jisheng, Su Caihong. Response of a hypersonic blunt cone boundary layer to slow acoustic waves with assessment of various routes of receptivity[J]. Applied Mathematics and Mechanics, 2018, 39(11): 1643−1660. doi: 10.1007/s10483-018-2391-6

Wan Bingbing, Su Caihong, Chen Jianqiang. Receptivity of a hypersonic blunt cone: role of disturbances in entropy layer[J]. AIAA Journal, 2020, 58(9): 4047−4054. doi: 10.2514/1.J058816

Ba Weitao, Niu Menghao, Su Caihong. Hypersonic boundary-layer receptivity over circular cones with ellipsoidal/spherical noses[J]. AIAA Journal, 2023, 61(2): 518−533. doi: 10.2514/1.J061846

Hammerton P W, Kerschen E J. Effect of nose bluntness on leading-edge receptivity[R]. 1992. doi: 10.1007/978-1-4612-2956-8_43

Hammerton P W, Kerschen E J. Boundary-layer receptivity for a parabolic leading edge[J]. Journal of Fluid Mechanics, 1996, 310: 243−267. doi: 10.1017/s0022112096001796

Egorov I, Fedorov A, Nechaev A. Receptivity of supersonic boundary layer on a blunt plate to acoustic disturbances[C]//Proc of the 42nd AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada. Reston, Virginia: AIAA, 2004: 249. doi: 10.2514/6.2004-249

Niu Menghao. Receptivity and transition prediction of hypersonic conical boundary layer[D]. Tianjin: Tianjin University, 2023(in Chinese).

Niu Menghao, Su Caihong. Receptivity and its influence on transition prediction of a hypersonic boundary layer over a small bluntness cone[J]. Physics of Fluids, 2023, 35(3): 034109. doi: 10.1063/5.0141000

Fedorov A V. Receptivity of a high-speed boundary layer to acoustic disturbances[J]. Journal of Fluid Mechanics, 2003, 491: 101−129. doi: 10.1017/S0022112003005263

Huang Jiahao, Zhao Lei, Zhao Rui. Local receptivity based on harmonic linearized Navier-Stokes equations[J]. Acta Aerodynamica Sinica, 2024, 42(3): 69−82(in Chinese). doi: 10.7638/kqdlxxb-2023.0068

Zhang Shuhai, Zhu Jun, Shu C W. A brief review on the convergence to steady state solutions of Euler equations with high-order WENO schemes[J]. Advances in Aerodynamics, 2019, 1(1): 16. doi: 10.1186/s42774-019-0019-2

Wan Bingbing. Study on sensitivity of hypersonic blunt body boundary layer considering entropy layer[D]. Tianjin: Tianjin University, 2018(in Chinese).

Malik M R, Chuang S, Hussaini M Y. Accurate numerical solution of compressible, linear stability equations[J]. Zeitschrift für Angewandte Mathematik und Physik, 1982, 33: 189−201.

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Numerical simulation of the effect of transition position on static and dynamic aerodynamic characteristics of cones

Intermodal exchange and wall temperature effect in a supersonic boundary layer

Progresses in engineering application research on hypersonic flow stability and transition

Progress in key scientific problems of hypersonic boundary-layer transition prediction: receptivity, evolution of disturbances and transition criterion

Local scattering theory for transition prediction in boundary-layer flows

Related Author

WAN Zhao

HE Kun

ZHANG Yifeng

CHEN Qi

Wang Xinguang

SONG Mingzhen

SU Caihong

DUAN Maochang

Related Institution

China Aerodynamics Research and Development Center, Mianyang

Laboratory for High-speed Aerodynamics, School of Mechanical Engineering, Tianjin University

Department of Mechanics, School of mechanical engineering, Tianjin University

State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center

School of Aeronautics, Northwestern Polytechnical University, Xi'an

AI问答

⁰