Investigation on test technique for hypersonic flow-through model nozzle outlet airflow parameters measurement

Shu Haifeng; He Chao; Guo Leitao; Xu Xiaobin; Fan Xiaohua

doi:10.11729/syltlx20160018

Volume 31 Issue 6

Turn off MathJax

Article Contents

Article Navigation > Journal of Experiments in Fluid Mechanics > 2017 > 31(6): 86-92, 99

Shu Haifeng, He Chao, Guo Leitao, et al. Investigation on test technique for hypersonic flow-through model nozzle outlet airflow parameters measurement[J]. Journal of Experiments in Fluid Mechanics, 2017, 31(6): 86-92, 99. doi: 10.11729/syltlx20160018

Citation:

PDF( 14154 KB)

Investigation on test technique for hypersonic flow-through model nozzle outlet airflow parameters measurement

doi: 10.11729/syltlx20160018

Shu Haifeng^{1
,
,},
He Chao¹,
Guo Leitao¹,
Xu Xiaobin^{1, 2},
Fan Xiaohua¹

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

Received Date: 2017-04-14
Rev Recd Date: 2017-06-22
Publish Date: 2017-12-25

Abstract

Abstract

The accurate measurement of hypersonic flow-through model nozzle outlet airflow parameters is significant for the estimation of the inner flow path aerodynamic characteristics. The presently available test methods are not satisfactory. A new test technique for measuring the outlet parameters is investigated, using a lifting body with air-breathing inlet, but without rudders, elevators and all stabilizers. The interference of two static tubes at different distances and the possible measurement error caused by the angle of airflow and static tube were studied by CFD. And a three degrees of freedom pressure measurement device was developed. The tests at Mach 6 were conducted to measure the nozzle wall pressure, static pressure and pitot pressure of nozzle outlet in Φ1m hypersonic wind tunnel of CARDC. Results indicate that the temperature of the nozzle outlet wall has significant impact on the repeatability of the measurement. When the distance between the nozzle outlet wall and the pressure harrow is less than six times of the static pressure tube diameter, the accuracy of the static pressure measurement would decrease.
- inner flow path,
- air-breathing hypersonic vehicle,
- pitot pressure,
- static pressure,
- wind tunnel test

FullText(HTML)

References(8)

References

[1]	McClinton C R, Hunt J L. Air breathing hypersonic technology vision vehicles and development dreams[R]. AIAA-99-4987, 1999. http://dl.acm.org/citation.cfm?id=887857
[2]	乐嘉陵.吸气式高超声速技术研究进展[J].推进技术, 2010, 31(6):641-649. http://d.wanfangdata.com.cn/Conference/6591556 Le J L. Progress in air-breathing hypersonic technology[J]. Journal of Propulsion Technology, 2010, 31(6):641-649. http://d.wanfangdata.com.cn/Conference/6591556
[3]	白菡尘, 王泽江.高超声速冲压发动机-飞行器计力体系讨论[J].推进技术, 2012, 33(1):1-6. http://d.wanfangdata.com.cn/Periodical/tjjs201201001 Bai H C, Wang Z J. Discussion on force-accounting system for airbreathing hypersonic vehicle[J]. Journal of Propulsion Technology, 2012, 33(1):1-6. http://d.wanfangdata.com.cn/Periodical/tjjs201201001
[4]	张红英, 程克明, 伍贻兆.某高超飞行器流道冷流特征及气动力特性研究[J].空气动力学学报, 2009, 27(1):119-123. http://www.cnki.com.cn/Article/CJFDTOTAL-KQDX200901022.htm Zhang H Y, Cheng K M, Wu Y Z. A study on the flowpath and the aerodynamic characteristic of a hypersonic vehicle[J]. Acta Aerodynamic Sinca, 2009, 27(1):119-123. http://www.cnki.com.cn/Article/CJFDTOTAL-KQDX200901022.htm
[5]	骆晓臣, 张堃元.侧压式进气道内部阻力分析[J].推进技术, 2007, 28(2):204-207. http://d.wanfangdata.com.cn/Periodical/tjjs200702021 Luo X C, Zhang K Y. Analysis for internal drag in sidewall-compression inlet[J]. Journal of Propulsion Technology, 2007, 28(2):204-207. http://d.wanfangdata.com.cn/Periodical/tjjs200702021
[6]	范洁川.风洞试验手册[M].北京:航空工业出版社, 2002. Fan J C. Handbook of wind tunnel test[M]. Beijing:Aviation Industry Press, 2002.
[7]	黄湛, 王宏伟, 张妍, 等.高超声速飞行器DPIV内流阻力测量技术研究[J].推进技术, 2014, 35(4):456-462. http://d.wanfangdata.com.cn/Periodical/tjjs201404004 Huang Z, Wang H W, Zhang Y, et al. Research of internal drag DPIV measurement for hypersonic Vehicle[J]. Journal of Propulsion Technology, 2014, 35(4):456-462. http://d.wanfangdata.com.cn/Periodical/tjjs201404004
[8]	许晓斌, 舒海峰, 谢飞, 等.通气模型内流道阻力直接测量技术研究[J].推进技术, 2013, 34(3):311-315. http://kns.cnki.net/KCMS/detail/detail.aspx?filename=tjjs201303004&dbname=CJFD&dbcode=CJFQ 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://kns.cnki.net/KCMS/detail/detail.aspx?filename=tjjs201303004&dbname=CJFD&dbcode=CJFQ