Experimental study on instability streak structure over a hypersonic cone

SHA Xinguo; GUO Yue; JI Feng; YUAN Xiangjiang; SHEN Qing

doi:10.7638/kqdlxxb-2019.0141

English Version Journal Login

您当前的位置：

首页 >

文章列表页 >

Experimental study on instability streak structure over a hypersonic cone

更新时间：2026-05-28

- Experimental study on instability streak structure over a hypersonic cone
- Vol. 38, Issue 1, Pages: 143-147(2020)
- 作者机构：
  
  中国航天空气动力技术研究院,北京,100074
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2019.0141
  CLC： V211.3
- Published：2020
- 稿件说明：
移动端阅览
沙心国, 郭跃, 纪锋, 袁湘江, 沈清. 高超声速圆锥边界层失稳条纹结构实验研究[J]. 空气动力学学报, 2020, 38(1): 143-147.

SHA Xinguo, GUO Yue, JI Feng, et al. Experimental study on instability streak structure over a hypersonic cone[J]. 2020, 38(1): 143-147.
沙心国, 郭跃, 纪锋, 袁湘江, 沈清. 高超声速圆锥边界层失稳条纹结构实验研究[J]. 空气动力学学报, 2020, 38(1): 143-147. DOI： 10.7638/kqdlxxb-2019.0141.

SHA Xinguo, GUO Yue, JI Feng, et al. Experimental study on instability streak structure over a hypersonic cone[J]. 2020, 38(1): 143-147. DOI： 10.7638/kqdlxxb-2019.0141.

摘要

边界层转捩的准确预测是高超声速飞行面临的关键气动问题之一。为研究高超声速边界层失稳和转捩机理，以前缘半径1.6mm、半锥角7°的圆锥模型为研究对象，在FD-07高超声速风洞中采用红外热图技术开展边界层转捩实验测量。通过与工程计算结果对比，确认模型表面边界层流态。实验结果表明：有迎角条件下，模型表面中后段出现条纹结构，条纹结构的起始位置随着周向角的增加而向上游移动；随着迎角的增加，条纹起始位置向上游移动，条纹强度差异和条纹与模型中心线的夹角越来越大。实验获得的条纹结构与不同频率扰动波相互作用直接数值模拟获得的条纹结构现象一致。通过对比分析，认为边界层内不同频率扰动波相互作用是产生条纹结构的一种机制。

Abstract

Boundary layer transition prediction is one of the key aerodynamic issues for hypersonic flight. In order to study the transition mechanism

a 7° half angle cone with nose radius of 1.6mm was experimented using infrared thermography (IR) in the hypersonic wind tunnel FD-07 at China Academy of Aerospace Aerodynamics. The heat flux obtained by IR was compared with that by the engineering method to confirm the boundary layer state on the model surface. The results show that streaks arise on the model surface at an angle of attack

the streaks starting position move upstream with circumferential angle increasing

and the attack angle have a big effect on the streaks distribution. Streaks obtained by the wind tunnel test present good agreement with the direct numerical simulation

it can conclude that the interaction of different frequency disturbances in the boundary layer is one of the mechanisms for generating the streaks.

关键词

Keywords

references

YU P, DUAN Y, CHEN J. Some aerodynamic issues in hypersonic flight[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(1):7-23. (in Chinese)

ANDERSON J D. Hypersonic and high temperature gas dynamics[M]. McGraw-Hill Book Company, 1989.

WANG S N, HAN Z H, SONG W P. A data-driven transition predication method for flows over airfoils[J]. Physics of Gases, 2017, 2(3):5-16. (in Chinese)

ZHOU L, YAN C, HAO Z H, et al. Transition model and transition criteria for hypersonic boundary layer flow[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(1):7-23. (in Chinese)

QIN Q, HAN Q. Prediction method of cross-flow instabilities-induced transition based on Spalart-Allmaras- γ - Re _( θt ) transition model[J ] . Physics of Gases, 2016, 1(3):19-24. (in Chinese)

DUAN Z W, XIAO Z X, FU S. Direct numerical simulation of hypersonic transition induced by an isolated cylindrical roughness element[J]. Science China (Physics, Mechanics Astronomy), 2014, 57(12):2330-2345.

LI F, YANG W B, WANG Q, et al. Status of ground test for hypersonic aerodynamics and its new challenge[J]. Physics of Gases, 2016, 1(2):1-9. (in Chinese)

MCDEVITT J B, MELLENTHIN J A. Upwash patterns on ablating and nonablating cones at hypersonic speeds[R]. NASA Technical Note TN-D-5346, 1969.

SWANSON E O, SCHNEIDER S P. Boundary-layer transition on cones at angle of attack in a Mach-6 quiet tunnel[R]. AIAA 2010-1062, 2010.

WARD C, HENDERSON R, SCHNEIDER S. Possible secondary instability of stationary crossflow vortices on an inclined cone at Mach 6[R]. AIAA 2015-2773, 2015.

EDELMAN J B, SCHNEIDER S P. Secondary instabilities of hypersonic stationary crossflow waves[R]. AIAA Paper 2016-3343.

EDELMAN J, CASPER K M, HENFLING J, et al. Crossflow transition on a pitched cone at Mach 8[C]//47th AIAA Fluid Dynamics Conference. 2017: 4299.

MUÑOZ F, HEITMANN D, RADESPIEL R. Instability modes in boundary layers of an inclined cone at Mach 6[R]. AIAA 2012-2823, 2012.

HEITMANN D, RADESPIEL R E. Hypersonic transition experiments in 3D cone flow with new measurement techniques[R]. Technical Univ Braunschweig (Germany) Inst of Fluid Mechanics, 2012.

WILLEMS S, GVLHAN A, JULIANO T J, et al. Laminar to turbulent transition on the HIFiRE-1 cone at Mach 7 and high angle of attack[C]//52nd Aerospace Sciences Meeting. 2014: 0428.

CRAIG S A, SARIC W S. Crossflow instability in a hypersonic boundary layer[J]. Journal of Fluid Mechanics, 2016, 808:224-244.

BERRIDGE D, CHOU A, WARD C, et al. Hypersonic boundary-layer transition experiments in a Mach 6 quiet tunnel[R]. AIAA 2010-1061, 2010.

BERRIDGE D, WARD C, LUERSEN R, et al. Boundary-layer instability measurements in a Mach-6 quiet tunnel[R]. AIAA 2012-3147, 2012.

CHEN X, ZHU Y, LEE C. Interactions between second mode and low-frequency waves in a hypersonic boundary layer[J]. Journal of Fluid Mechanics, 2017, 820:693-735.

SIVASUBRAMANIAN J, FASEL H F. Direct numerical simulation of transition in a sharp cone boundary layer at Mach 6:fundamental breakdown[J]. Journal of Fluid Mechanics, 2015, 768:175-218.

SIVASUBRAMANIAN J, HERMANN F. Direct numerical simulation of laminar-turbulent transition in a flared cone boundary layer at Mach 6[R]. AIAA 2016-0846, 2016.

JI F, GUAN F, SHEN Q. An interferential streak instability of boundary layer over a cone at Mach 6[C]//51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. 2013: 525.

CARLOMAGNO G M, CARDONE G. Infrared thermography for convective heat transfer measurements[J]. Exp Fluids, 2010, 49:1187-1218.

JI F, XIE S F, SHEN Q. Hypersonic high frequency (1 MHz) fluctuation pressure testing technology and application[J]. Acta Aerodynamica Sinica, 2016, 34(5):587-591. (in Chinese)

JIANG G Q, LIU L Y. Heat transfer of hypersonic gas and ablation thermal protection[M]. Beijing:National defense industry press, 2003. (in Chinese)

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

Experimental study of noise reduction design for a fully acoustically lined, low-turbulence, low-noise engineering wind tunnel

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

Optimal growth and secondary instability of hypersonic blunt wedge boundary layers

Evolution and development of flow transition and supersonic modes under high-temperature gas effects

Related Author

Chen Jianqiang

Tu Guohua

Wan Bingbing

Li Chenhui

Chen Yining

ZHANG Aozhe

LIU Peiqing

CHEN Yue

Related Institution

School of Aeronautic Science and Engineering, Beihang University, Beijing

State Key Laboratory of Aerodynamics, Mianyang

Beijing KOAK Acoustics Laboratory, Beijing

Key Laboratory of Aero-Acoustics Ministry of Industry and Information Technology, Beihang University, Beijing

China Aerodynamics Research and Development Center, Mianyang

AI问答

⁰