Experimental study on influence of incoming total temperature on hypersonic boundary layer transition

LI Qiang; WAN Bingbing; ZHUANG Yu; ZHAO Jinshan

doi:10.11729/syltlx20220081

Turn off MathJax

Article Contents

Abstract

References

LI Q, WAN B B, ZHUANG Y, et al. Experimental study on influence of incoming total temperature on hypersonic boundary layer transition[J]. Journal of Experiments in Fluid Mechanics, doi: 10.11729/syltlx20220081.

Citation:

PDF (8505 KB)

Experimental study on influence of incoming total temperature on hypersonic boundary layer transition

1.
Computational Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang　621000, China
2.
Hypervelocity Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang　621000, China

More Information

Received Date: August 21, 2022
Revised Date: February 01, 2023
Accepted Date: February 06, 2023
Available Online: June 06, 2023

Graphical Abstract

Abstract

Abstract

Wall-temperature-ratio/temperature is a parameter that needs attention in the study of hypersonic boundary layer transition. The boundary layer transition experiment was carried out in CARDC Φ2 m shock tunnel, the model is a 7° half-angle cone model with the nosetip bluntness of 0.05mm, the Mach number is 9.86 and 9.97, the unit Reynolds number is 8.9 × 10⁶/m and 8.4 × 10⁶/m, and the total temperature is 1332.2 K and 956.6 K, respectively. Under the conditions of approximately the same Mach number, Reynolds number, noise level and wall temperature, the effect of the total temperature of the wind tunnel on the transition of the hypersonic boundary layer is studied. The heat flux sensor is used to measure the transition position and the high frequency fluctuation pressure sensor is used to measure the fluctuation characteristics of the boundary layer. The experimental results are compared with the transition prediction results of the γ−Re_θ−MT model and the linear stability theory results, respectively. The heat flux distribution results of the cone calculated by the transition model are in good agreement with the wind tunnel test results, and the transition positions obtained experimentally and theoretically are basically the same, indicating that the numerical calculation method of the transition model has high reliability. The pressure fluctuation results measured by the PCB sensor and the theoretical analysis results of the linear stability are mutually confirmed, showing the second mode wave spectrum characteristics of the two cases of high and low total temperature under wind tunnel conditions.
- transition,
- wind tunnel test,
- fluctuation characteristic,
- total incoming flow temperature,
- linear stability

FullText(HTML)

References (27)

References

[1]	SCHNEIDER S P. Flight data for boundary-layer transition at hypersonic and supersonic speeds[J]. Journal of Spacecraft and Rockets, 1999, 36(1): 8–20. doi: 10.2514/2.3428
[2]	BERRY S A, HORVATH T J, HOLLIS B R, et al. X-33 hypersonic boundary layer transition[R]. AIAA 99-3560, 1999. doi: 10.2514/6.1999-3560
[3]	MALIK M, ZANG T, BUSHNELL D. Boundary layer transition in hypersonic flows[R]. AIAA 90-5232, 1990. DOI: 10.2514/6.1990-5232
[4]	LIN T C, GRABOWSKY W R, YELMGREN K E. The search for optimum configurations for re-entry vehicles[J]. Journal of Spacecraft and Rockets, 1984, 21(2): 142–149. doi: 10.2514/3.8625
[5]	WHITEHEAD A. NASP aerodynamics[R]. AIAA 89-5013, 1989.
[6]	ERICSSON L. Effect of boundary-layer transition on vehicle dynamics[C]//Proc of the 7th Aerospace Sciences Meeting. 1969. doi: 10.2514/6.1969-106
[7]	MARTELLUCCI A, NEFF R. The influence of asymmetric transition on re-entry vehicle motion[C]//Proc of the Guidance, Control and Flight Mechanics Conference. 1970. doi: 10.2514/6.1970-987
[8]	HOLDEN M. Studies of the effects of transitional and turbulent boundary layers on the aerodynamic performance of hypersonic re-entry vehicles in high Reynolds number flows[R]. Calspan Report AB-5834-A-2, 1978.
[9]	罗纪生. 高超声速边界层的转捩及预测[J]. 航空学报, 2015, 36(1): 357–372. LUO J S. Transition and prediction for hypersonic boundary layers[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(1): 357–372.
[10]	ZHAO L, YU G T, LUO J S. Extension of e^N method to general three-dimensional boundary layers[J]. Applied Mathematics and Mechanics, 2017, 38(7): 1007–1018. doi: 10.1007/s10483-017-2215-6
[11]	陈坚强, 涂国华, 张毅锋, 等. 高超声速边界层转捩研究现状与发展趋势[J]. 空气动力学学报, 2017, 35(3): 311–337. DOI: 10.7638/kqdlxxb-2017.0030 CHEN J Q, TU G H, ZHANG Y F, et al. Hypersnonic boundary layer transition: what we know, where shall we go[J]. Acta Aerodynamica Sinica, 2017, 35(3): 311–337. doi: 10.7638/kqdlxxb-2017.0030
[12]	涂国华, 万兵兵, 陈坚强, 等. MF-1钝锥边界层稳定性及转捩天地相关性研究[J]. 中国科学 (物理学力学天文学), 2019, 49(12): 114–124. TU G H, WAN B B, CHEN J Q, et al. Investigation on correlation between wind tunnel and flight for boundary layer stability and transition of MF-1 blunt cone[J]. Scientia Sinica (Physica, Mechanica & Astronomica), 2019, 49(12): 114–124.
[13]	陈坚强, 涂国华, 万兵兵, 等. HyTRV流场特征与边界层稳定性特征分析[J]. 航空学报, 2021, 42(6): 124317. CHEN J Q, TU G H, WAN B B, et al. Characteristics of flow field and boundary-layer stability of HyTRV[J]. Acta Aeronautica et Astronautica Sinica, 2021, 42(6): 124317.
[14]	国义军, 周宇, 肖涵山, 等. 飞行试验热流辨识和边界层转捩滞后现象[J]. 航空学报, 2017, 38(10): 121255. DOI: 10.7527/S1000-6893.2017.121255 GUO Y J, ZHOU Y, XIAO H S, et al. Delay phenomenon of boundary layer transition according to heating flux identified from flight test[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(10): 121255. doi: 10.7527/S1000-6893.2017.121255
[15]	CHEN J Q, YI S H, LI X L, et al. Theoretical, numerical and experimental study of hypersonic boundary layer transition: blunt circular cone[J]. Applied Thermal Engineering, 2021, 194: 116931. doi: 10.1016/j.applthermaleng.2021.116931
[16]	TUFTS M W, BORG M P, GOSSE R C, et al. Collaboration between flight test, ground test, and computation on HIFiRE-5[C]//Proc of the 2018 Applied Aerodynamics Conference. 2018. doi: 10.2514/6.2018-3807
[17]	KIMMEL R L, ADAMCZAK D W, BORG M P, et al. First and fifth hypersonic international flight research experimentation’s flight and ground tests[J]. Journal of Spacecraft and Rockets, 2019, 56(2): 421–431. doi: 10.2514/1.a34287
[18]	GOSSE R, KIMMEL R. CFD study of three-dimensional hypersonic laminar boundary layer transition on a Mach 8 elliptic cone[C]//Proc of the 39th AIAA Fluid Dynamics Conferenc. 2009. doi: 10.2514/6.2009-4053
[19]	MACK L M. Linear stability theory and the problem of supersonic boundary- layer transition[J]. AIAA Journal, 1975, 13(3): 278–289. doi: 10.2514/3.49693
[20]	MACK L. M. Boundary-layer linear stability theory[R]. AGARD Report No. 709, 1984.
[21]	MALIK M R. Prediction and control of transition in supersonic and hypersonic boundary layers[J]. AIAA Journal, 1989, 27(11): 1487–1493. doi: 10.2514/3.10292
[22]	MADDALON D V. Effect of varying wall temperature and total temperature on transition Reynolds number at Mach 6.8[J]. AIAA Journal, 1969, 7(12): 2355–2357. doi: 10.2514/3.5549
[23]	STETSON K F, KIMMEL R L. Surface temperature effects on boundary-layer transition[J]. AIAA Journal, 1992, 30(11): 2782–2783. doi: 10.2514/3.11300
[24]	LEITH POTTER J. Review of the influence of cooled walls on boundary-layer transition[J]. AIAA Journal, 1980, 18(8): 1010–1012. doi: 10.2514/3.7703
[25]	ZHAO J S, LIU S, ZHAO L, et al. Numerical study of total temperature effect on hypersonic boundary layer transition[J]. Physics of Fluids, 2019, 31(11): 1–25. doi: 10.1063/1.5125116
[26]	李强, 江涛, 陈苏宇, 等. 激波风洞边界层转捩测量技术及应用[J]. 航空学报, 2019, 40(8): 122740. DOI: 10.7527/S1000-6893.2019.22740 LI Q, JIANG T, CHEN S Y, et al. Measurement technique and application of boundary layer transition in shock tunnel[J]. Acta Aeronautica et Astronautica Sinica, 2019, 40(8): 122740. doi: 10.7527/S1000-6893.2019.22740
[27]	李强, 万兵兵, 杨凯, 等. 高超声速尖锥边界层压力脉动和热流脉动特性试验[J]. 航空学报, 2022, 43(2): 12956. DOI: 10.7527/S1000-6893.2020.24956 LI Q, WAN B B, YANG K, et al. Experimental research on characteristics of pressure and heat flux fluctuation in hypersonic cone boundary layer[J]. Acta Aeronautica et Astronautica Sinica, 2022, 43(2): 12956. doi: 10.7527/S1000-6893.2020.24956

[1]	XIA Huihui, ZHANG Shunping, YANG Shunhua, KAN Ruifeng, XU Zhenyu, RUAN Jun, YAO Lu, HUANG An. Two-dimensional distribution measurement of direct-connect scramjet combustion flow field based on TDLAS multi-absorption lines[J]. Journal of Experiments in Fluid Mechanics, 2025, 39(1): 80-86. DOI: 10.11729/syltlx20220103
[2]	CHENG Xiaoqi, FAN Ziye, TANG Zhanqi, BAI Jianxia, JIANG Nan. Experimental investigation of the spatial distribution of uniform momentum zones in wall-bounded flow[J]. Journal of Experiments in Fluid Mechanics, 2024, 38(4): 21-28. DOI: 10.11729/syltlx20230132
[3]	LI Long, PENG Lei, ZHAO Wei. Study of liquid spreading and particle size distribution during the preparation of aluminum alloy powder by rotary disc atomization[J]. Journal of Experiments in Fluid Mechanics. DOI: 10.11729/syltlx20230059
[4]	CHEN Shuyue, GUO Xiangdong, WANG Zixu, LIU senyun, WU Yingchun. Preliminary research on size measurement of supercooled large droplet in icing wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2021, 35(3): 22-29. DOI: 10.11729/syltlx20200104
[5]	LI Fangji, ZHAO Qing, FAN Jianchao, JIA Shuang, RONG Xiangsen, GUO Min. Technology research and test verification of distributed flow regulator for inlet test in wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2020, 34(4): 74-80. DOI: 10.11729/syltlx20190022
[6]	Ma Wenyong, Wang Guanya, Zheng Xi, Chen Tie, Li Zhi, Zhang Chengyuan, Fang Pingzhi. Effects of end condition on aerodynamic force distribution on a skewed circular cylinder[J]. Journal of Experiments in Fluid Mechanics, 2019, 33(2): 43-50. DOI: 10.11729/syltlx20180050
[7]	Liu Lu, Cao Wei. Stability and transition prediction of the hypersonic plate boundary layers for wall temperature distribution[J]. Journal of Experiments in Fluid Mechanics, 2018, 32(6): 41-48. DOI: 10.11729/syltlx20180107
[8]	Wu Liyin, Zhang Kouli, Li Chenyang, Li Qinglian. Model for three-dimensional distribution of liquid fuel in supersonic crossflows[J]. Journal of Experiments in Fluid Mechanics, 2018, 32(4): 20-30. DOI: 10.11729/syltlx20170172
[9]	Zhang Jing, Zheng Xu, Wang Leilei, Cui Haihang, Li Zhanhua. Experimental study on the characteristic motion of bubble propelled hollow Janus microspheres[J]. Journal of Experiments in Fluid Mechanics, 2017, 31(2): 61-66. DOI: 10.11729/syltlx20160152
[10]	An Yali, Xu Zhipeng, Liu Tiejun, Xie Dailiang. Experimental study on flowrate measurement of air-water two phase flow by double-cone flowmeter[J]. Journal of Experiments in Fluid Mechanics, 2016, 30(5): 67-73. DOI: 10.11729/syltlx20160044

Cited By

Cited by

Periodical cited type(6)

1.	刘奇，刘常青，李增军. 超声速风洞模型冲击载荷抑制装置设计. 航空动力学报. 2023(02): 364-370 .
2.	王珏，王誉超，季辰. 超声速风洞带舵机状态全尺寸舵颤振亚临界试验. 空天防御. 2023(02): 77-83 .
3.	Chuanwei XUAN，Jinglong HAN，Bing ZHANG，Haiwei YUN，Xiaomao CHEN. Hypersonic flutter and flutter suppression system of a wind tunnel model. Chinese Journal of Aeronautics. 2019(09): 2121-2132 .
4.	周波，涂清，高川. 超声速风洞模型插入机构控制系统设计. 测控技术. 2019(12): 122-125+135 .
5.	周波，高川，杨洋. 2m超声速风洞流场变速压控制方法研究. 实验流体力学. 2019(06): 72-77 . 本站查看
6.	季辰，赵玲，朱剑，刘子强，李锋. 高超声速风洞连续变动压舵面颤振试验. 实验流体力学. 2017(06): 37-44 . 本站查看

Other cited types(1)

Get Citation

PDF

XML

Article Metrics

Article views (204) PDF downloads (28) Cited by(7)

Experimental study on influence of incoming total temperature on hypersonic boundary layer transition

Abstract

References

Related Articles

Cited by

Periodical cited type(6)

Other cited types(1)

Catalog

Article Metrics

Related

Experimental study on influence of incoming total temperature on hypersonic boundary layer transition

Abstract

References

Related Articles

Cited by

Periodical cited type(6)

Other cited types(1)

Catalog

Article Metrics

Related

Export File

Citation

Format

Content