Research progress on aerodynamic test technology of hypersonic wind tunnel for air-breathing aerocraft

Xu Xiaobin; Shu Haifeng; Xie Fei; Wang Xiong; Guo Leitao

doi:10.11729/syltlx20180053

Volume 32 Issue 5

Turn off MathJax

Article Contents

Abstract

References

Journal of Experiments in Fluid Mechanics > 2018 > 32(5): 29-40. > DOI: 10.11729/syltlx20180053

Xu Xiaobin, Shu Haifeng, Xie Fei, Wang Xiong, Guo Leitao. Research progress on aerodynamic test technology of hypersonic wind tunnel for air-breathing aerocraft[J]. Journal of Experiments in Fluid Mechanics, 2018, 32(5): 29-40. DOI: 10.11729/syltlx20180053

Citation:

PDF (10657 KB)

Research progress on aerodynamic test technology of hypersonic wind tunnel for air-breathing aerocraft

1.
Hypervelocity Aerodynamics Institute of China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China
2.
Science and Technology on Scramjet Laboratory of Hypervelocity Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

More Information

Received Date: April 11, 2018
Revised Date: July 22, 2018

Graphical Abstract

Abstract

Abstract

To get accurate wind tunnel test results with high precision for the airframe/propulsion integrated air-breathing hypersonic flight vehicles, reliable wind tunnel test techniques must be developed according to the vehicle's special configuration and structure. To satisfy the requirements of hypersonic wind tunnel tests for those airframe/propulsion integrated vehicles, the flow-through model aerodynamic force measurement technique, rear-jet interference test technique, hinge-moment measurement technique, flow-through model dynamic derivative test technique, and the surface skin-friction measurement technique have been developed in hypersonic wind tunnels of CARDC(China Aerodynamics Research and Development Center), which give massive support to those efforts to get authentic hypersonic wind tunnel test results for the design and evaluation of airframe/propulsion integrated air-breathing hypersonic flight vehicles.
- hypersonic wind tunnel,
- frame-propulsion integrated,
- air-breathing vehicle,
- aerodynamic force measurement,
- wind tunnel testing

FullText(HTML)

References (35)

References

[1]	Holland S D, Woods W C, Engeluand W C. Hyper-X research vehicle experimental aerodynamics test program overview[J]. Journal of Spacecraft and Rockets, 2001, 38(6):828-835. DOI: 10.2514/2.3772
[2]	Engeluand W C, Holland S D, Charles E C Jr. Aerodynamic datebase development for the Hyper-X airframe integrated scramjet propulsion experiments[R]. AIAA-2000-4006, 2000.
[3]	罗金玲, 李超, 徐锦.高超声速飞行器机体/推进一体化设计的启示[J].航空学报, 2015, 36(1):39-48. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=hkxb201501005 Luo J L, Li C, Xu J. Inspiration of hypersonic vehicle with airframe/propulsion integrated design[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(1):39-48. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=hkxb201501005
[4]	吴颖川, 贺元元, 贺伟, 等.吸气式高超声速飞行器机体推进一体化技术研究进展[J].航空学报, 2015, 36(1):245-260. http://d.old.wanfangdata.com.cn/Periodical/hkxb201501020 Wu Y C, He Y Y, He W, et al. Progress in airframe-propulsion integration technology of airbreathing hypersonic vehicle[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(1):245-260. http://d.old.wanfangdata.com.cn/Periodical/hkxb201501020
[5]	恽起麟.实验空气动力学[M].北京:国防工业出版社, 1991.
[6]	恽起麟.风洞试验[M].北京:国防工业出版社, 2002.
[7]	许晓斌.常规高超声速风洞与试验技术[M].北京:国防工业出版社, 2015.
[8]	赵忠良, 杨晓娟, 蒋卫民, 等.高超声速飞行器通流模拟方法与风洞验证技术[J].航空学报, 2014, 35(11):2932-2938. http://d.old.wanfangdata.com.cn/Periodical/hkxb201411004 Zhao Z L, Yang X J, Jiang W M, et al. Through-flow simulation method and wind tunnel validation technique for hypersonic vehicle[J]. Acta Aeronautica et Astronautica Sinica, 2014, 35(11):2932-2938. http://d.old.wanfangdata.com.cn/Periodical/hkxb201411004
[9]	金亮, 柳军, 罗世彬, 等.高超声速一体化飞行器冷流状态气动特性研究[J].实验流体力学, 2010, 24(1):42-45. DOI: 10.3969/j.issn.1672-9897.2010.01.008 Jin L, Liu J, Luo S B, et al. Aerodynamic characterization of an integrated hypersonic vehicle[J]. Journal of Experiments in Fluid Mechanics, 2010, 24(1):42-45. DOI: 10.3969/j.issn.1672-9897.2010.01.008
[10]	吴军强, 徐明方, 张毅峰.带多个进气道的导弹通气模型测力试验技术研究[J].流体力学实验与测量, 2000, 14(3):52-56. DOI: 10.3969/j.issn.1672-9897.2000.03.010 Wu J Q, Xu M F, Zhang Y F. Force measurement test technique research of flow through model of the multi-inlet missile[J]. Experiments and Measurements in Fluid Mechanics, 2000, 14(3):52-56. DOI: 10.3969/j.issn.1672-9897.2000.03.010
[11]	张红英, 程克明, 伍贻兆.高超声速飞行器内流道流态及其对全机气动力影响的实验研究[J].空气动力学学报, 2009, 27(2):193-198. DOI: 10.3969/j.issn.0258-1825.2009.02.009 Zhang H Y, Cheng K M, Wu Y Z. Experimental study of flow characteristics and the influence for a hypersonic flight vehicle[J]. Acta Aerodynamica Sinica, 2009, 27(2):193-198. DOI: 10.3969/j.issn.0258-1825.2009.02.009
[12]	Stephen M R, Ethiraj V, Earl R K, et al. Hypersonic single expansion ramp nozzle simulation[J]. Journal of Spacecraft and Rockets, 1992, 29(6):749-755. DOI: 10.2514/3.25527
[13]	Hirschen C, Gülhan A, Beck W, et al. Experimental study of the interaction between internal and external flows of a scramjet nozzle using various diagnostic techniques[R]. AIAA-2007-5088, 2007.
[14]	Huebner L D, Witte D W, Andrews E H Jr. Exhaust simulation testing of a hypersonic air-breathing model at transonic speeds[R]. AIAA-2003-7001, 2003.
[15]	贺旭照, 秦思, 曾学军, 等.模拟飞行条件下的吸气式高超声速飞行器后体尾喷流干扰问题实验方案研究[J].推进技术, 2014, 35(10):1310-1316. http://d.old.wanfangdata.com.cn/Conference/8358929 He X Z, Qin S, Zeng X J, et al. Experiment scheme research on afterbody nozzle plume interference of air-breathing hyper-sonic vehicle fly condition[J]. Journal of Propulsion Technology, 2014, 35(10):1310-1316. http://d.old.wanfangdata.com.cn/Conference/8358929
[16]	曾庆华, 黄琳, 夏智勋, 等.发动机喷流对飞行器飞行姿态影响的研究[J].宇航学报, 2002, 23(4):73-76. DOI: 10.3321/j.issn:1000-1328.2002.04.015 Zeng Q H, Huang L, Xia Z X, et al. The simulation of nozzle exhaust effects on aircraft's flight attitude[J]. Journal of Astronautics, 2002, 23(4):73-76. DOI: 10.3321/j.issn:1000-1328.2002.04.015
[17]	林敬周, 田正雨, 王志坚.三维高超声速底部喷流干扰流场数值模拟与试验研究[J].实验流体力学, 2006, 20(4):49-53. DOI: 10.3969/j.issn.1672-9897.2006.04.009 Lin J Z, Tian Z Y, Wang Z J. Numerical and experimental study of base jet interaction in hypersonic external flow[J]. Journal of Experiments in Fluid Mechanics, 2006, 20(4):49-53. DOI: 10.3969/j.issn.1672-9897.2006.04.009
[18]	孙振华, 吴催生, 徐东来.导弹尾流对后弹体影响的CFD仿真分析[J].弹箭与制导学报, 2011, 31(3):157-159, 168. DOI: 10.3969/j.issn.1673-9728.2011.03.046 Sun Z H, Wu C S, Xu D L. CFD study of the effect of rocket plume on thermal environment of aft-missile[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2011, 31(3):157-159, 168. DOI: 10.3969/j.issn.1673-9728.2011.03.046
[19]	司芳芳, 袁先旭, 李建强, 等.推力转向喷流与高速主流干扰参数影响规律的数值模拟研究[J].空气动力学学报, 2012, 30(5):583-591. http://d.old.wanfangdata.com.cn/Periodical/kqdlxxb201205005 Si F F, Yuan X X, Li J Q, et al. The study of parameters' infection between vectoring jet and high speed main flows interaction[J]. Acta Aerodynamica Sinica, 2012, 30(5):583-591. http://d.old.wanfangdata.com.cn/Periodical/kqdlxxb201205005
[20]	许晓斌, 舒海峰, 谢飞, 等.通气模型内流道阻力直接测量技术[J].推进技术, 2013, 34(3):311-315. http://d.old.wanfangdata.com.cn/Periodical/tjjs201303005 Xu X B, Shu H F, Xie F, et al. Technique investigation on flow-through model inner-flow drag straightway measured by strain-gauge balance[J]. Journal of Propulsion Technology, 2013, 34(3):311-315. http://d.old.wanfangdata.com.cn/Periodical/tjjs201303005
[21]	许晓斌, 舒海峰, 徐筠, 等.升力体飞行器尾喷流模拟气动力试验方法研究[J].空气动力学学报, 2016, 34(1), 86-90. http://d.old.wanfangdata.com.cn/Periodical/kqdlxxb201601015 Xu X B, Shu H F, Xu Y, et al. Experimental investigation on lifting body aerodynamic force with simulated aft-body jet[J]. Acta Aerodynamica Sinica, 2016, 34(1), 86-90. http://d.old.wanfangdata.com.cn/Periodical/kqdlxxb201601015
[22]	李周复.风洞特种试验技术[M].北京:航空工业出版社, 2010.
[23]	熊琳, 刘展, 陈河梧.铰链力矩天平技术及其在高超声速风洞的应用研究[J].实验流体力学, 2007, 21(3):54-57. DOI: 10.3969/j.issn.1672-9897.2007.03.011 Xiong L, Liu Z, Chen H W. Hinge moment balance technique and application in hypersonic wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2007, 21(3):54-57. DOI: 10.3969/j.issn.1672-9897.2007.03.011
[24]	陈丽, 赵协和, 刘维亮, 等.提高测量最大铰链力矩试验数据精准度的有效模拟技术研究[J].流体力学实验与测量, 2002, 16(3):51-56. DOI: 10.3969/j.issn.1672-9897.2002.03.009 Chen L, Zhao X H, Liu W L, et al. Simulation technique for improving data precision and accuracy of maximum hinge moment test[J]. Experiments and Measurements in Fluid Mechanics, 2002, 16(3):51-56. DOI: 10.3969/j.issn.1672-9897.2002.03.009
[25]	刘绪, 赵云飞, 王东方, 等.高超声速内外流一体化飞行器动态特性[J].弹道学报, 2013, 25(3):38-43. DOI: 10.3969/j.issn.1004-499X.2013.03.008 Liu X, Zhao Y F, Wang D F, et al. Dynamic characteristics of hypersonic integrative vehicle with internal and external flow[J]. Journal of Ballistics, 2013, 25(3):38-43. DOI: 10.3969/j.issn.1004-499X.2013.03.008
[26]	唐志共.高超声速气动力试验[M].北京:国防工业出版社, 2004.
[27]	袁先旭, 陈琦, 谢昱飞, 等.动导数数值预测中的相关问题[J].航空学报, 2016, 37(8):2385-2394. http://d.old.wanfangdata.com.cn/Periodical/hkxb201608005 Yuan X X, Chen Q, Xie Y F, et al. Problems in numerical prediction of dynamic stability derivatives[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(8):2385-2394. http://d.old.wanfangdata.com.cn/Periodical/hkxb201608005
[28]	郭雷涛. Ф1米高超声速风洞动导数试验技术研究[D].绵阳: 中国空气动力研究与发展中心, 2013. Guo L T. Investigation on dynamic derivative test technique in Ф1m hypersonic wind tunnel[D]. Mianyang: China Aero-dynamics Research and Development Center, 2013.
[29]	陈建中, 赵忠良, 范长海, 等. 2m量级高速风洞强迫振动动导数试验技术研究[J].空气动力学学报, 2016, 34(5):598-605. http://d.old.wanfangdata.com.cn/Periodical/kqdlxxb201605009 Chen J Z, Zhao Z L, Fan C H, et al. Forced-oscillation dynamic derivative test techniques in 2 meter scale high speed wind tunnels[J]. Acta Aerodynamica Sinica, 2016, 34(5):598-605. http://d.old.wanfangdata.com.cn/Periodical/kqdlxxb201605009
[30]	潘金柱, 张杰, 才义, 等.高速风洞动导数试验精准度提升研究[J].空气动力学学报, 2016, 34(5):606-610. http://d.old.wanfangdata.com.cn/Periodical/kqdlxxb201605010 Pan J Z, Zhang J, Cai Y, et al. Investigation on the high-speed wind tunnel dynamic derivative test accuracy promotion[J]. Acta Aerodynamica Sinica, 2016, 34(5):606-610. http://d.old.wanfangdata.com.cn/Periodical/kqdlxxb201605010
[31]	Silvester T B, Morgan R G. Skin-friction measurements and flow establishment within a long duct at super orbital speeds[J]. AIAA Journal, 2008, 46(2):527-536. DOI: 10.2514/1.32668
[32]	吕治国, 李国君, 赵荣娟, 等.激波风洞高超声速摩阻直接测量技术研究[J].实验流体力学, 2013, 27(6):81-85. DOI: 10.3969/j.issn.1672-9897.2013.06.015 Lyu Z G, Li G J, Zhao R J, et al. Direct measurement of skin friction at hypersonic shock tunnel[J]. Journal of Experiments in Fluid Mechanics, 2013, 27(6):81-85. DOI: 10.3969/j.issn.1672-9897.2013.06.015
[33]	马洪强, 高贺, 毕志献.高超声速飞行器相关的摩擦阻力直接测量技术[J].实验流体力学, 2011, 25(4):83-88. DOI: 10.3969/j.issn.1672-9897.2011.04.016 Ma H Q, Gao H, Bi Z X. Direct measurement of skin friction for hypersonic flight vehicle[J]. Journal of Experiments in Fluid Mechanics, 2011, 25(4):83-88. DOI: 10.3969/j.issn.1672-9897.2011.04.016
[34]	Meloy J, Griffin J, Sells J, et al. Experimental verification of a MEMS based skin friction sensor for quantitative wall shear stress measurement[R]. AIAA-2011-3995, 2011.
[35]	刘凯.金属基多梁圆盘式敏感质量加速度计相关技术研究[D].上海: 上海交通大学, 2009. http://cdmd.cnki.com.cn/Article/CDMD-10248-1013003577.htm Liu K. Related techniques of micro-accelerometer based on metal and multi-beam disc mass[D]. Shanghai: Shanghai Jiaotong University, 2009. http://cdmd.cnki.com.cn/Article/CDMD-10248-1013003577.htm

Cited By

Cited by

Periodical cited type(18)

1.	韩笑，高创，郑怡彤，刘小兵. 切角凹槽矩形截面桥塔的气动特性试验研究. 石家庄铁道大学学报(自然科学版). 2024(01): 9-15+23 .
2.	白桦，刘博祥，姬乃川，李加武. 节段模型二元端板合理尺寸估算方法. 振动与冲击. 2023(02): 312-320 .
3.	王仰雪，刘庆宽，靖洪淼，李震，孙一飞. 倾斜栏杆对流线型箱梁涡激振动性能影响的试验研究. 振动与冲击. 2023(06): 232-239+254 .
4.	于畅，仇法梅，田学东，杨群，刘小兵. 圆角矩形柱平均气动力特性的雷诺数效应试验研究. 石家庄铁道大学学报(自然科学版). 2023(02): 29-34 .
5.	杨群，于畅，刘小兵，刘庆宽. 不同圆角率的方形断面斯特罗哈数的雷诺数效应研究. 振动与冲击. 2023(11): 223-231 .
6.	刘庆宽，王仰雪，孙一飞，李震，韩原，靖洪淼. 栏杆高度对流线型箱梁涡振性能影响的试验研究. 湖南大学学报(自然科学版). 2023(07): 140-150 .
7.	刘路路，杨皓然，邹云峰，何旭辉，韩艳，陈志强. 公铁同层双幅非对称主梁气动干扰特性研究. 铁道科学与工程学报. 2023(10): 3861-3872 .
8.	杨群，于畅，于文文，刘小兵. 圆角方柱气动特性的风洞试验研究. 振动与冲击. 2023(24): 59-68 .
9.	韩振，李波，甄伟，杨庆山，田玉基. 宽厚比为5的超高层建筑风荷载特性研究. 哈尔滨工程大学学报. 2022(02): 196-202 .
10.	张庆华，马文勇，杨杰，张彦，周帅伟. 不同风倾角下典型等边角钢静风力风洞试验研究. 振动工程学报. 2022(02): 277-283 .
11.	白桦，王涵，姬乃川，李加武. 节段模型长宽比对风洞测力试验及计算分析的影响. 中国公路学报. 2022(08): 202-212 .
12.	杨群，刘庆宽，韩瑞，刘小兵. 不同圆角率的方形断面气动特性的雷诺数效应. 振动与冲击. 2020(04): 150-156 .
13.	沈国辉，姚剑锋，郭勇，邢月龙，楼文娟. 直径30 cm圆柱的气动力参数和绕流特性研究. 振动与冲击. 2020(06): 22-28 .
14.	温青，池俊豪，华旭刚，王修勇，孙洪鑫. 端部条件和展弦比对矩形断面节段模型气动力特征的影响. 实验流体力学. 2020(04): 36-43 . 本站查看
15.	任若松，梁新华，刘小兵，马文勇，刘庆宽. 准流线型桥梁断面气动力特性的雷诺数效应研究. 工程力学. 2020(S1): 139-144+167 .
16.	李海飞，梁新华，孙一飞，崔会敏，刘庆宽. 流线型桥梁断面表面脉动风荷载特性研究. 工程力学. 2020(S1): 242-248+260 .
17.	马文勇，汪冠亚，郑熙，陈铁，李智，张程远，方平治. 端部状态对斜置圆柱气动力分布的影响. 实验流体力学. 2019(02): 43-50 . 本站查看
31.	杨群，刘庆宽，孙亚松，刘小兵. 圆角方形断面气动特性试验. 振动.测试与诊断. 2020(01): 140-147+208 .

Other cited types(16)

Get Citation

PDF

XML

Article Metrics

Article views (622) PDF downloads (99) Cited by(34)

Research progress on aerodynamic test technology of hypersonic wind tunnel for air-breathing aerocraft

Abstract

References

Cited by

Periodical cited type(18)

Other cited types(16)

Catalog

Article Metrics

Related

Export File

Citation

Format

Content