Intermodal exchange and wall temperature effect in a supersonic boundary layer

SU Caihong; SONG Mingzhen

doi:10.7638/kqdlxxb-2019.0048

English Version Journal Login

您当前的位置：

首页 >

文章列表页 >

Intermodal exchange and wall temperature effect in a supersonic boundary layer

更新时间：2026-05-28

- Intermodal exchange and wall temperature effect in a supersonic boundary layer
- Vol. 38, Issue 6, Pages: 1056-1063(2020)
- 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：
- 基金信息：
- DOI：10.7638/kqdlxxb-2019.0048
  CLC： O357.4
- Published：2020
- 稿件说明：
移动端阅览
苏彩虹, 宋明真. 超声速边界层中的模态转换及壁温影响效应[J]. 空气动力学学报, 2020, 38(6): 1056-1063.

SU Caihong, SONG Mingzhen. Intermodal exchange and wall temperature effect in a supersonic boundary layer[J]. 2020, 38(6): 1056-1063.
苏彩虹, 宋明真. 超声速边界层中的模态转换及壁温影响效应[J]. 空气动力学学报, 2020, 38(6): 1056-1063. DOI： 10.7638/kqdlxxb-2019.0048.

SU Caihong, SONG Mingzhen. Intermodal exchange and wall temperature effect in a supersonic boundary layer[J]. 2020, 38(6): 1056-1063. DOI： 10.7638/kqdlxxb-2019.0048.

摘要

对于马赫数大于4的超声速边界层，Mack第二模态起主导作用。根据感受性的研究，生成第二模态的一个重要途径是，边界层内的快模态在下游演化过程中因相速度“同步”而发生模态转换。采用数值方法研究了超声速平板边界层中快模态到第二模态波的模态转换过程，通过定义模态转换系数和模态转换区间，建立了适用于多个不同壁面温度条件下的模态转换系数和转换区间与扰动频率之间的模型公式。在此基础上，基于线性稳定性理论，发展了包含模态转换过程的扰动演化的计算方法，并采用抛物化稳定性方程进行了验证。结果表明，在较广泛的壁面温度条件下，该方法可以准确计算包含快模态到第二模态转换过程的幅值演化。该方法由于考虑了第二模态的生成机制，比原有的基于线性理论的转捩预测方法更加具有物理依据。

Abstract

At free-stream Mach number larger than 4

the second mode is the dominant instability mode in supersonic boundary layers. According to the findings from receptivity research

one important way to generate the second mode is through intermodal exchange

by which the excited fast mode in the boundary layer synchronizes with the second mode when travels downstream. In this paper

the intermodal exchange between the fast mode and the second mode in a supersonic boundary layer is investigated numerically. Two coefficients

i.e. the amplitude and region of intermodal exchange are defined. Their relations are established with respect to the disturbance frequency. Based on linear stability theory

a new method accounting for the intermodal exchange is developed to compute the evolutions of the disturbances. The parabolized stability equations is used to verify the new method. It is shown that

under a wide range of wall temperature conditions

the newly developed method can accurately predict the evolutions of the disturbance considering the process of intermodal exchange between fast mode and the second mode. With considerations of the initial amplitude of the excited fast mode and a transition criterion

this method can be easily used to predict transition of a boundary layer. Since it considers the generation of the second mode through intermodal exchange

it accounts for more physics than the conventional transition prediction method.

关键词

Keywords

references

REED H L, PEREZ E, KUEHL J, et al. Verification and validation issues in hypersonic stability and transition prediction[J]. Journal of Spacecraft and Rockets, 2015, 52(1):29-37. DOI:10.2514/1.a32825

CHEN J Q, TU G H, ZHANG Y F, et al. Hypersonic 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

LUO J S. Transition and prediction for hypersonic boundary layers[J].Acta Aeronautica et Astronautica Sinica, 2015, 36(1):357-372.(in Chinese) DOI:10.7527/S1000-6893.2014.0244

SU C H. The reliability of the improved eN method for the transition prediction of boundary layers on a flat plate[J]. Science China Physics, Mechanics and Astronomy, 2012, 55(5):837-843.

MACK L M. Boundary-layer linear stability theory[R]. AGARD Rep.709. California: Jet Propulsion Laboratory, California Institute of Technology, 1984.

SU C H, ZHOU H. Transition prediction of a hypersonic boundary layer over a cone at small angle of attack:with the improvement of e-N method[J]. Science in China Series G:Physics, Mechanics and Astronomy, 2009, 52(1):115-123. DOI:10.1007/s11433-009-0006-4

SU C H, ZHOU H. Transition prediction for supersonic and hypersonic boundary layers on a cone with angle of attack[J]. Science in China Series G:Physics, Mechanics and Astronomy, 2009, 52(8):1223-1232. DOI:10.1007/s11433-009-0162-6

SU C H, ZHOU H. Transition prediction of the supersonic boundary layer on a cone under the consideration of receptivity to slow acoustic waves[J]. Science China Physics, Mechanics and Astronomy, 2011, 54(10):1875-1882. DOI:10.1007/s11433-011-4472-0

KING R A. Three-dimensional boundary-layer transition on a cone at Mach 3.5[J ] . Experiments in Fluids, 1992, 13(5): 305-314. DOI: 10.1007/BF00209502

GOLDSTEIN M E. The evolution of Tollmien-Sclichting waves near a leading edge[J]. Journal of Fluid Mechanics, 1983, 127:59-81. DOI:10.1017/s002211208300261x

GOLDSTEIN M E. Scattering of acoustic waves into Tollmien-Schlichting waves by small streamwise variations in surface geometry[J]. Journal of Fluid Mechanics, 1985, 154:509-529. DOI:10.1017/s0022112085001641

RUBAN A I. On the generation of Tollmien-Schlichting waves by sound[J]. Fluid Dynamics, 1985, 19(5):709-717. DOI:10.1007/bf01093536

FEDOROV A V, KHOKHLOV A P. Prehistory of instability in a hypersonic boundary layer[J]. Theoretical and Computational Fluid Dynamics, 2001, 14(6):359-375. DOI:10.1007/s001620100038

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

FEDOROV A. Transition and stability of high-speed boundary layers[J]. Annual Review of Fluid Mechanics, 2011, 43(1):79-95. DOI:10.1146/annurev-fluid-122109-160750

MA Y B, ZHONG X L. 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 Y B, ZHONG X L. Receptivity of a supersonic boundary layer over a flat plate. Part 2. Receptivity to free-stream sound[J ] . Journal of Fluid Mechanics, 2003, 488: 79-121. DOI: 10.1017/s0022112003004798

GAO J, LUO J S, WU X S. Receptivity of hypersonic boundary layer due to fast-slow acoustics interaction[J]. Acta Mechanica Sinica, 2015, 31(6):899-909. DOI:10.1007/s10409-015-0504-8

WAN BB, LUO J S, SU C H. 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

MA Y B, ZHONG X L. Receptivity of a supersonic boundary layer over a flat plate. Part 3. Effects of different types of free-stream disturbances[J]. Journal of Fluid Mechanics, 2005, 532:63-109. DOI:10.1017/s0022112005003836

BALAKUMAR P. Receptivity of hypersonic boundary layers to acoustic andvortical disturbances (invited)[C ] //Proc of the 45th AIAA Fluid Dynamics Conference, Dallas, TX. Reston, Virginia: AIAA, 2015. DOI: 10.2514/6.2015-2473

GAO J. The method of the stability analysis and receptivity to acoustics in supersonic boundary layers[D]. Tianjin: Tianjin University, 2014.(in Chinese)

ZHANG Y M. Applications of PSE to evolution of disturbances in compressible boundary layers and to secondary instability in supersonic boundary layers[D]. Tianjin: Tianjin University, 2008.(in Chinese)

ZHANG Y M, ZHOU H. Verification of parabolized stability equations for its application to compressible boundary layers[J]. Applied Mathematics and Mechanics, 2007, 28(8):987-998. DOI:10.1007/s10483-007-0801-3

ZHANG Y M, ZHOU H. PSE as applied to problems of transition in compressible boundary layers[J]. Applied Mathematics and Mechanics, 2008, 29(7):833-840. DOI:10.1007/s10483-008-0701-8

ZANG T A, CHANG C L, NG L L. The transition prediction toolkit: LST, SIT, PSE, DNS, and LES[C]//Fifth Symposium on Numerical and Physical Aspects of Aerodynamic Flows, 1992.

LIU J X, ZHANG S L, FU S. Linear spatial instability analysis in 3D boundary layers using plane-marching 3D-LPSE[J]. Applied Mathematics and Mechanics, 2016, 37(8):1013-1030. DOI:10.1007/s10483-016-2114-8

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

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

Study on hypersonic forebody transition characteristics based on the amplification factor transport model

Linear stability analysis based on neural network

Transition prediction of boundary layers over an engine nacelle with different outer covers

Effects of chemical non-equilibrium models on stability analysis of blunt wedge boundary layer with high enthalpy

Related Author

Chen Yining

Li Chenhui

Wan Bingbing

Tu Guohua

Chen Jianqiang

Huang Hexia

Xu Yuan

Wang Haiyang

Related Institution

School of Aeronautic Science and Engineering, Beihang University, Beijing

State Key Laboratory of Aerodynamics, Mianyang

College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing

School of Mechanical Engineering, Tianjin University, Tianjin

School of Aeronautics, Northwestern Polytechnical University, Xi'an

AI问答

⁰