钝锥体辐射平衡温度不确定度量化分析

doi:10.7527/S1000-6893.2023.28673

Abstract

Abstract:

For long-range thermal tests in a combustion-heated hypersonic wind tunnel， it is necessary to quantify the uncertainty of the radiation equilibrium temperature distribution of the test model caused by the random fluctuation of the test conditions and identify the critical factors for engineering application. This study selects the total temperature of the experimental air flow， model emissivity， and model position as the input variables affecting the radiation equilibrium temperature distribution of the model by numerical simulation. The stochastic expansion between input parameters and radiation equilibrium temperature is established by the point-collocation Non-Intrusive Polynomial Chaos （NIPC） method. Uncertainties of radiation equilibrium temperature caused by random variation of the input variables are quantified. The results indicate that the radiation equilibrium temperature uncertainty of the blunt cone is the largest at the shoulder， which is 10.33%， and the uncertainty of the large area of the cone is 6.5%-7%. The sensitivity analysis reveals that the total temperature could significantly influence the uncertainty of the radiation equilibrium temperature in the stagnation area， while the model position has little influence on the uncertainty of the radiation equilibrium temperature distribution.

Key words: hypersonic wind tunnel, aerodynamic heating, radiation equilibrium temperature, uncertainty quantification, sensitivity analysis

CLC Number:

V211

Zhenkang ZHANG, Wanwu XU, Zhiyan LI, Wei YE. Uncertainty quantification analysis of blunt cone radiation equilibrium temperature[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(15): 528673.

Figures/Tables 19

Fig.1

Fig.2

Fig.3

Table 1

Fig.4

Fig.5

Table 2

Fig.6

Fig.7

Fig.8

Fig.9

Fig.10

Fig.11

Table 3

Fig.12

Fig.13

Fig.14

Fig.15

Fig.16

References 24

1	苟建军，肖爽，胡嘉欣，等. 高超声速飞行器气动热耗散、输运以转换技术研究进展［J］. 宇航学报， 2022， 43（8）： 984-999.
	GOU J J， XIAO S， HU J X， et al. Research progress of aerodynamic heat dissipation， transport and conversion technologies of hypersonic vehicles［J］. Journal of Astronautics， 2022， 43（8）： 984-999 （in Chinese）.
2	师昆仑，邱云龙，陈伟芳，等. 传感器局部温度差异对压缩拐角热流测量的影响［J］. 航空学报， 2020， 41（12）： 124055.
	SHI K L， QIU Y L， CHEN W F， et al. Influence of local temperature difference of sensors on heat flow measurement of compression corner［J］. Acta Aeronautica et Astronautica Sinica， 2020， 41（12）： 124055 （in Chinese）.
3	朱广生，聂春生，曹占伟，等. 气动热环境试验及测量技术研究进展［J］. 实验流体力学， 2019， 33（2）： 1-10.
	ZHU G S， NIE C S， CAO Z W， et al. Research progress of aerodynamic thermal environment test and measurement technology［J］. Journal of Experiments in Fluid Mechanics， 2019， 33（2）： 1-10 （in Chinese）.
4	马正雪，罗振兵，赵爱红，等. 高超声速流场等离子体合成射流逆向喷流特性［J］. 航空学报， 2022， 43（S2）： 727747.
	MA Z X， LUO Z B， ZHAO A H， et al. Reverse jet characteristics of plasma synthetic jet in hypersonic flow field［J］. Acta Aeronautica et Astronautica Sinica， 2022， 43（S2）： 325-345 （in Chinese）.
5	ZHU Y H， PENG W， XU R N， et al. Review on active thermal protection and its heat transfer for airbreathing hypersonic vehicles［J］. Chinese Journal of Aeronautics， 2018， 31（10）： 1929-1953.
6	谌君某，陈星，毕志献. 高焓激波风洞试验技术综述［J］. 空气动力学学报， 2018， 36（4）： 543-554.
	SHEN J M， CHEN X， BI Z X. Review on experimental technology of high enthalpy shock tunnel［J］. Acta Aerodynamica Sinica， 2018， 36（4）： 543-554 （in Chinese）.
7	周勇为，易仕和，程忠宇. 高超声速风洞调试和流场校测［J］.国防科技大学学报，2009，31（6）： 57-61.
	ZHOU Y W， YI S H， CHENG Z Y. The test and calibration of hypersonic wind tunnel［J］. Journal of National University of Defense Technology， 2009， 31（6）： 57-61 （in Chinese）.
8	WADHAMS T， MUNDY E， MACLEAN M. Ground test studies of the HIFiRE-1 transition experiment Part 1： Experimental results［J］. Journal of Spacecraft and Rockets， 2008， 45（6）： 1134-1148.
9	REES T W， BRUCE P， FISHER T B， et al. Merrifield numerical and experimental studies of the hypersonic flow around a cube at incidence［J］. Acta Astronautica， 2021，183： 75-88.
10	SUDARSHAN B， JAGADEESH G， SARAVANAN S， Experimental investigation on aerothermal effects of forward-facing cylindrical and parabolic cavity in hypersonic ﬂow ［J］. Acta Astronautica， 2021，185： 226-235.
11	MICHAL S， JOSEF K. Double probe recovery temperature anemometry［J］. Thermal Science and Engineering Progress， 2021， 23： 100875.
12	KUMAR S， MAHULIKAR S P. Aero-thermal analysis of lifting body configurations in hypersonic flow［J］. Acta Astronautica， 2016， 126： 382-394.
13	BÖHRK H， DITTERT C， WEIHS H. Sharp leading edge at hypersonic flight： Modeling and flight measurement［J］. Journal of spacecraft and rockets， 2014： 53（5）：1753-1760.
14	ZHAO Y T， CHAO Y， WANG X Y. Uncertainty and sensitivity analysis of SST turbulence model on hypersonic flow heat transfer［J］. International Journal of Heat and Mass Transfer， 2019，136： 808-820.
15	向星皓，张毅锋，陈坚强，等. 横流转捩模型参数不确定度量化分析与应用研究［J］. 宇航学报， 2020，41（9）：1141-1150.
	XIANG Z H， ZHANG Y F， CHEN J Q， et al. Uncertainty quantification analysis and application research on cross flow transition model parameters［J］. Journal of Astronautics， 2020， 41（9）： 1141-1150 （in Chinese）.
16	SIMON F， GUILLEN P， SAGAUT P， et al. A PC-based approach to uncertain transonic aerodynamics［J］. Computer Methods in Applied Mechanics and Engineering，2010， 299：1091-1099.
17	张伟，王小永，于剑，等. 来流导致的高超声速气动热不确定度量化分析［J］. 北京航空航天大学学报， 2018， 44（5）： 1102-1109.
	ZHANG W， WANG X Y， YU J， et al. Uncertainty quantification analysis in hypersonic aerodynamics due to freestream［J］. Journal of Beijing University of Aeronautics and Astronautics， 2018， 44（5）： 1102-1109 （in Chinese）.
18	MENTER F R. Two-equation eddy-viscosity turbulence models for engineering applications ［J］. AIAA Journal， 1994， 32（8）：1598-1605.
19	刘传振，孟旭飞，刘荣健，等. 双后掠乘波体高超声速试验与数值分析［J］. 航空学报， 2022， 43（9）： 126015.
	LIU C Z， MENG X F， LIU R J， et al. Experimental and numerical investigation of hypersonic performance of double swept waverider［J］. Acta Aeronautica et Astronautica Sinica， 2022， 43（9）： 126015 （in Chinese）.
20	WIETING A R. Experimental study of shock wave interference heating on a cylindrical leading edge［R］. 1987.
21	张智超，高振勋，蒋崇文，等. 高超声速气动热数值计算壁面网格准则［J］. 北京航空航天大学学报， 2015， 41（4）： 594-600.
	ZHANG Z C， GAO Z X， JIANG C W， et al. Grid generation criterions in hypersonic aeroheating computations［J］. Journal of Beijing University of Aeronautics and Astronautics， 2015， 41（4）： 594-600 （in Chinese）.
22	闫文辉，任立磊. 计算网格对气动力气动热数值模拟影响的研究［J］. 航空计算技术， 2017， 47（2）： 1-4.
	YAN W H， REN L L. Grid study on numerical of aerodynamic flowfield［J］. Aeronautical Computing Technique， 2017， 47（2）： 1-4 （in Chinese）.
23	SMIRNOV N N， BETELIN V B， NIKITIN V F. Accumulation of errors in numerical simulations of chemically reacting gas dynamics［J］. Acta Astronautica， 2015， 117：338–355.
24	刘坤伟. 燃烧加热污染组分对高超气动/推进性能影响研究［D］. 合肥：中国科学技术大学，2016： 31-59.
	LIU K W. Study on the influence of combustion preheating vitiation on hypersonic aero-propulsion performance［D］. Hefei： University of Science and Technology of China， 2016： 31-59 （in Chinese）.

参数	数值
气流总温/K	1 712
气流总压/MPa	5.72
湍流强度/%	5
气流组分质量分数	8%H₂O，13%CO₂，23%O₂，56%N₂

参数	网格1	网格2	网格3
S₁	2.92×10^-6	1.95×10^-6	1.37×10^-6
S₂	2.92×10^-6	1.95×10^-6	1.37×10^-6
S₃	5.78×10^-10	1.57×10^-10	7.23×10^-11
S_err	5.83×10^-5	3.91×10^-6	2.74×10^-6
S_max	0.01	0.01	0.01
n_ac	100 000	100 000	100 000
n_max	2.94×10⁶	6.55×10⁶	1.32×10⁷
R_s	29.41	65.33	132.85

参数	基准值	变化下限	变化上限
气流总温/K	1 712	1 512	1 712
模型发射率	0.7	0.6	0.8
模型位置/mm	0	-377.8	377.8

[1]	Guoliang RONG, Yifan YANG, Chuangchuang LI, Zhiyuan LI, Xueliang LI, Jiaquan ZHAO, Jie WU. Integrated design of homogeneous mixing and heating of flow based on dual-throat Ludwieg tube wind tunnel settling chamber [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(9): 130906-130906.
[2]	Zhouwei FAN, Chuihuan KONG, Ming LIU, Zhaoguang TAN. Sensitivity analysis on key parameters of hybrid hydrogen fuel cell commercial aircraft [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(9): 631066-631066.
[3]	Luoyu RAO, Tao ZHANG, Chongguang SHI, Chengxiang ZHU, Yancheng YOU. Effects of sideslip angle on shock wave interference structure of V-shaped blunt leading edge [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(2): 130681-130681.
[4]	Shanyue GUAN, Zhengyu TIAN, Wenjia XIE, Qianyue FU, Yuhang CHU, Jiajun ZHU. Analysis of plasma chemical reactions of hypersonic reentry blunt in flight corridor [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(18): 131735-131735.
[5]	Yongxin SHI, Kuo TIAN, Bo WANG. Topology optimization of aerospace axisymmetric structures based on bidirectional density function [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(S1): 730585-730585.
[6]	Chunhua LI, Jianzhong SUN, Jilong LU. Maintenance-oriented approach for HPT blade life digital twin modeling [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(21): 629385-629385.
[7]	Le JIANG, Yibiao CHEN, Yanjun LI, Guilin LI, Tao LIU. Flow and separation characteristics of pressurized centrifugal separator for aero⁃engine [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(2): 128675-128675.
[8]	Tianyuan JI, Wuli CHU, Haoguang ZHANG, Zhengtao GUO, Dejun MENG. Effect of data-driven twist deviation on compressor performance [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(19): 629938-629938.
[9]	Yanhe TAO, Qintao GUO, Jin ZHOU, Jiaqian MA, Xiaofa LI. Efficient variational Bayesian model updating under observation uncertainty [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(19): 229969-229969.
[10]	Ming HUANG, Kaiyuan ZHANG, Zhigang LI, Jun LI. Uncertainty quantification of aerothermal performance of squealer tip with film cooling structure [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(19): 629979-629979.
[11]	Haowan ZHUANG, Chuanjun CAO, Yan WANG, Jinfang TENG, Mingmin ZHU, Xiaoqing QIANG. Uncertainty analysis of non-axisymmetric stagger angle based on NIPC [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(19): 630145-630145.
[12]	Zhendong GUO, Haojie LI, Liming SONG, Hualiang ZHANG, Zhao YIN. Robust optimization method based on adaptive sparse polynomial chaos [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(19): 630273-630273.
[13]	Limin GAO, Haohao WANG, Weina HUANG, Qiusheng LUO, Ruiyu LI, Guang YANG, Yue DAN, Chi MA, Baohai WU, Jiaqi LUO. Research progress on uncertainty effect of compressor blade machining deviation [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(19): 630386-630386.
[14]	Qingfa LUO, Qin YU, Gang LI, Dong WANG. Layout optimization of control sensors in environmental vibration test [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(18): 0-229843-.
[15]	Jiaxing ZHU, Yining LI, Shiyong NIU, Yisong TIAN, Di LI, Yiming XIE. Global numerical calculation of fluid-structure coupling of aero micro-relief valve based on CFD computation domain division coupling technology [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(15): 630202-630202.

Uncertainty quantification analysis of blunt cone radiation equilibrium temperature

RichHTML

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

Figures/Tables 19

References 24

Related Articles 15

Recommended Articles

Metrics

Comments