Experimental study on the aero-heating characteristics of waverider in the high enthalpy shock wave tunnel

Wang Xiaopeng; Zhang Chen'an; Zhai Jian; Wang Famin; Ye Zhengyin

doi:10.11729/syltlx20190080

Volume 33 Issue 4

Turn off MathJax

Article Contents

Abstract

References

Journal of Experiments in Fluid Mechanics > 2019 > 33(4): 52-57. > DOI: 10.11729/syltlx20190080

Wang Xiaopeng, Zhang Chen'an, Zhai Jian, Wang Famin, Ye Zhengyin. Experimental study on the aero-heating characteristics of waverider in the high enthalpy shock wave tunnel[J]. Journal of Experiments in Fluid Mechanics, 2019, 33(4): 52-57. DOI: 10.11729/syltlx20190080

Citation:

PDF (4443 KB)

Experimental study on the aero-heating characteristics of waverider in the high enthalpy shock wave tunnel

1.
National Key Laboratory of Aerodynamic Design and Research, Northwestern Polytechnical University, Xi'an 710072, China
2.
State Key Laboratory of High-Temperature Gas Dynamics, Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, China

More Information

Received Date: June 23, 2019
Revised Date: July 16, 2019

Graphical Abstract

Abstract

Abstract

Long-range aerodynamic heating is a key scientific problem. In this paper, the cone-derived waverider is designed firstly and then the characteristics of the heat flux distribution along the leading edge and on the lower surface of the waverider are studied by means of the high enthalpy wind tunnel test and the high temperature chemical non-equilibrium aerodynamic heating numerical calculation. Results show that:The high heat flux mainly concentrates on the small region around the stagnation point and the change of angle of attack (0°~6°) does not have an obvious effect on the high heat flux region at the leading edge, but it induces a significant increase of the heat flux on the lower surface. In addition, the change of the sideslip angle (0°~4°) has a significant effect on the heat flux at the leading edge, so it is not recommended to fly with a large sideslip angle.
- waverider,
- real gas effect,
- aero-heating,
- high enthalpy wind-tunnel test,
- numeri-cal simulation

FullText(HTML)

References (20)

References

[1]	吕红庆.乘波体结构热响应及防护问题研究[D].哈尔滨: 哈尔滨工程大学, 2010. http://cdmd.cnki.com.cn/article/cdmd-10217-1012266032.htm Lyu H Q. Study of thermal response and protection for waverider structure[D]. Harbin: Harbin Engineering Univer-sity, 2010. http://cdmd.cnki.com.cn/article/cdmd-10217-1012266032.htm
[2]	周印佳.乘波构型设计及表面热流计算[D].哈尔滨: 哈尔滨工程大学, 2012. http://cdmd.cnki.com.cn/Article/CDMD-10217-1012517871.htm Zhou Y J. Design of waverider configuration and calculation of heating rates on the surface[D]. Harbin: Harbin Engineering University, 2012. http://cdmd.cnki.com.cn/Article/CDMD-10217-1012517871.htm
[3]	刘建霞, 侯中喜, 陈小庆, 等.高超声速滑翔飞行器气动性能的数值模拟研究[J].国防科技大学学报, 2012, 34(4):22-27. DOI: 10.3969/j.issn.1001-2486.2012.04.005 Liu J X, Hou Z X, Chen X Q, et al. Numerical simulation on the aerodynamic performance of hypersonic glide vehicle[J]. Journal of National University of Defense Technology, 2012, 34(4):22-27. DOI: 10.3969/j.issn.1001-2486.2012.04.005
[4]	Liu J X, Hou Z X, Chen X Q, et al. Experimental and numerical study on the aero-heating characteristics of blunted waverider[J]. Applied Thermal Engineering, 2013, 51(1-2):301-314. DOI: 10.1016/j.applthermaleng.2012.09.026
[5]	杨建龙, 刘猛, 阿嵘, 等.高超声速热化学非平衡对气动热环境影响[J].北京航空航天大学学报, 2017, 43(10):2063-2072. http://d.old.wanfangdata.com.cn/Periodical/bjhkhtdxxb201710015 Yang J L, Liu M, A R. Influence of hypersonic thermo-chemical non-equilibrium on aerodynamic thermal environments[J]. Journal of Beijing University of Aeronautics and Astronau-tics, 2017, 43(10):2063-2072. http://d.old.wanfangdata.com.cn/Periodical/bjhkhtdxxb201710015
[6]	董维中, 丁明松, 高铁锁, 等.热化学非平衡模型和表面温度对气动热计算影响分析[J].空气动力学学报, 2013, 31(6):692-698. http://d.old.wanfangdata.com.cn/Periodical/kqdlxxb201306002 Dong W Z, Ding M S, Gao T S, et al. The influence of thermo-chemical non-equilibrium model and surface temperature on heat transfer rate[J]. Acta Aerodynamica Sinica, 2013, 31(6):692-698. http://d.old.wanfangdata.com.cn/Periodical/kqdlxxb201306002
[7]	Liu Z, Liu J, Ding F, et al. Effect of thermochemical non-equilibrium on the aerodynamics of an osculating-cone wave-rider under different angles of attack[J]. Acta Astronautica, 2017, 139:288-295. DOI: 10.1016/j.actaastro.2017.07.013
[8]	Liu J, Li K, Liu W Q. High-temperature gas effects on aerodynamic characteristics of waverider[J]. Chinese Journal of Aeronautics, 2015, 28(1):57-65. DOI: 10.1016/j.cja.2014.12.004
[9]	杨恺, 原志超, 朱强华, 等.高超声速热化学非平衡钝体绕流数值模拟[J].推进技术, 2014, 35(12):1585-1591. http://d.old.wanfangdata.com.cn/Conference/8155863 Yang K, Yuan Z C, Zhu Q H, el al. Numerical simulation of hypersonic thermochemical nonequilibrium blunt body flows[J]. Journal of Propulsion Technology, 2014, 35(12):1585-1591. http://d.old.wanfangdata.com.cn/Conference/8155863
[10]	Pezzella G, Votta R. Finite rate of chemistry effects on the high altitude aerodynamics of an apollo-shaped reentry capsule[R]. AIAA-2009-7306, 2009.
[11]	Gao Z X, Jiang C W, Lee C H. Aero-heating study of hypersonic chemical nonequilibrium flows around a reentry blunt body[R]. AIAA-2014-4415, 2014.
[12]	Hao J, Wang J Y, Lee C H. Numerical study of hypersonic flows over reentry configurations with different chemical nonequilibrium models[J]. Acta Astronautica, 2016, 126:1-10. DOI: 10.1016/j.actaastro.2016.04.014
[13]	Suzuki K, Abe T. Thermochemical nonequilibrium viscous shock-layer analysis for a Mars aerocapture vehicle[J]. Journal of Thermophysics and Heat Transfer, 1994, 8(4):773-780. DOI: 10.2514/3.611
[14]	Inger G R. Nonequilibrium boundary-layer effects on the aerodynamic heating of hypersonic waverider vehicles[J]. Journal of Thermophysics and Heat Transfer, 1995, 9(4):595-604. DOI: 10.2514/3.713
[15]	Inger G R. Non-equilibrium boundary layer effects on the aerodynamic heating of hypersonic vehicles[J]. Acta Astronau-tica, 1995, 36(4):205-216. DOI: 10.1016/0094-5765(95)00101-5
[16]	Starkey R P. Design of waverider based re-entry vehicles[R]. AIAA-2005-3390, 2005.
[17]	曾卫刚, 李维东, 王发民.平衡气体对乘波体气动力/热特性影响[J].空气动力学学报, 2012, 30(5):566-572, 605. http://www.cqvip.com/QK/95593X/201205/43755638.html Zeng W G, Li W D, Wang F M. Equilibrium gas effects on aerodynamic and aerothermal characteristics of waveriders[J]. Acta Aerodynamica Sinica, 2012, 30(5):566-572, 605. http://www.cqvip.com/QK/95593X/201205/43755638.html
[18]	耿永兵, 刘宏, 雷麦芳, 等.高升阻比乘波构型优化设计[J].力学学报, 2006, 38(4):540-546. DOI: 10.3321/j.issn:0459-1879.2006.04.014 Geng Y B, Liu H, Lei M F. Optimized design of waverider with high lift over drag ratio[J]. Chinese Journal of Theoretical and Applied Mechanics, 2006, 38(4):540-546. DOI: 10.3321/j.issn:0459-1879.2006.04.014
[19]	聂春生, 李宇, 黄建栋, 等.高超声速非平衡气动加热试验及数值分析研究[J].中国科学:技术科学, 2018, 48(8):845-852. http://www.cnki.com.cn/Article/CJFDTotal-JEXK201808004.htm Nie C S, Li Y, Huang J D, et al. Test of aero-heating in hypersonic non-equilibrium flow and numerical simulation study[J]. Scientia Sinica:Technologica, 2018, 48(8):845-852. http://www.cnki.com.cn/Article/CJFDTotal-JEXK201808004.htm
[20]	Gupta R N, Yos J M, Thompson R A, et al. A review of reaction rates and thermodynamic and transport properties for an 11-species air model for chemical and thermal nonequilibrium calculations to 30000K[R]. NASA-TM-101528, 1990.

Cited By

Cited by

Periodical cited type(2)

1.	杨凯，王辉，杨庆涛，朱新新，刘济春，陈苏宇. 超高速气动热风洞试验相关的热流标定技术. 气动研究与试验. 2025(01): 53-66 .
2.	陈苏宇，刘济春，杨凯，朱涛，朱新新，王辉. 薄膜热流计与原子层热电堆热流传感器的激波风洞试验对比. 实验流体力学. 2024(05): 90-97 . 本站查看

Other cited types(3)

Get Citation

PDF

XML

Article Metrics

Article views (238) PDF downloads (22) Cited by(5)

Experimental study on the aero-heating characteristics of waverider in the high enthalpy shock wave tunnel

Abstract

References

Cited by

Periodical cited type(2)

Other cited types(3)

Catalog

Article Metrics

Related

Experimental study on the aero-heating characteristics of waverider in the high enthalpy shock wave tunnel

Abstract

References

Cited by

Periodical cited type(2)

Other cited types(3)

Catalog

Article Metrics

Related

Export File

Citation

Format

Content