气体引射效应对壁面热流和摩擦阻力的影响

doi:10.7527/S1000-6893.2023.28587

Abstract

Abstract:

The ablative thermal protection material will be pyrolyzed under high thermal load. The produced pyrolysis gas is injected into the boundary layer， reducing heat flux and skin-friction drastically. Firstly， the boundary condition of wall mass injection is established， and the accuracy of this boundary is verified. After that， for the hypersonic blunt wedge model， the mechanisms of the influence of different angles of attack and different gases on the wall heat flux and skin-friction are studied. The numerical results show that due to the existence of wall mass injection， the distance of the windward detached shock from the wall increases， and the high-temperature region is pushed away from the wall， reducing the wall heat flux and skin-friction. Compared with air injection， the distance of the detached shock due to pyrolysis gas at the same mass flow rate is farther from the wall， and the temperature gradient， viscosity coefficient， and velocity gradient also decrease obviously in the boundary layer. Therefore， the reduction of heat flux and skin-friction by pyrolysis gas injection is more significant， and the efficiency of heat flux and skin-friction reduction increases with the decrease of the attack angle. Comparison of the results at different mass flow rates finds that the increase in air injection mass flow rate improves the efficiency of heat flux and skin-friction reduction， and the efficiencies of both is nearly equal when the air injection mass flow rate is twice that of the pyrolysis gas.

Key words: pyrolysis gas, wall mass injection, heat flux and skin-friction reduction, hypersonic, computational fluid dynamics

CLC Number:

V211.3

Yuxiang FAN, Rui ZHAO, Zhengxuan ZUO, Guang YANG, Yu LI. Gas⁃injection effects on wall heat flux and skin⁃friction of vehicles[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(21): 528587-528587.

Figures/Tables 21

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References 32

1	赵瑾，孙向春，张俊，等. 热防护材料气固界面传热传质问题研究进展［J］. 航空学报， 2022， 43（10）： 527577.
	ZHAO J， SUN X C， ZHANG J， et al. Research advances on heat and mass transfer coupling effect at gas-solid interface for thermal protection materials［J］. Acta Aeronautica et Astronautica Sinica， 2022， 43（10）： 527577 （in Chinese）.
2	叶友达. 高超声速空气动力学研究进展与趋势［J］. 科学通报， 2015， 60（12）： 1095-1103.
	YE Y D. Advances and prospects in hypersonic aerodynamics［J］. Chinese Science Bulletin， 2015， 60（12）： 1095-1103 （in Chinese）.
3	李海燕，唐志共，杨彦广，等. 高超声速飞行器高温流场数值模拟面临的问题［J］. 航空学报， 2015， 36（1）： 176-191.
	LI H Y， TANG Z G， YANG Y G， et al. Problems of numerical simulation of high-temperature gas flow fields for hypersonic vehicles［J］. Acta Aeronautica et Astronautica Sinica， 2015， 36（1）： 176-191 （in Chinese）.
4	董维中，高铁锁，丁明松，等. 高超声速飞行器表面温度分布与气动热耦合数值研究［J］. 航空学报， 2015， 36（1）： 311-324.
	DONG W Z， GAO T S， DING M S， et al. Numerical study of coupled surface temperature distribution and aerodynamic heat for hypersonic vehicles［J］. Acta Aeronautica et Astronautica Sinica， 2015， 36（1）： 311-324 （in Chinese）.
5	LAUB B， VENKATAPATHY E. Thermal protection system technology and facility needs for demanding future planetary missions［C］∥ International Workshop on Planetary Probe Atmospheric Entry and Descent Trajectory Analysis and Science. Paris： European Space Agency， 2004： 239-247.
6	王筠，杨云华，冯志海. 深空探测用热防护材料的现状及发展方向［J］. 宇航材料工艺， 2013， 43（5）： 1-10.
	WANG Y， YANG Y H， FENG Z H. Current status and further trend of thermal protection materials for deep space exploration［J］. Aerospace Materials & Technology， 2013， 43（5）： 1-10 （in Chinese）.
7	JOHNSON S M. Thermal protection materials： Development， characterization and evaluation： ARC-E-DAA-TN5732［R］. Washington， D.C.： NASA， 2012.
8	REYNIER P. Convective blockage during Earth re-entry： A review［C］∥ 40th AIAA Thermophysics Conference. Reston： AIAA， 2008.
9	REYNIER P. Survey of convective blockage for planetary entries［J］. Acta Astronautica， 2013， 83： 175-195.
10	BREWER R A， BRANT D N. Thermal protection system for the Galileo mission atmospheric entry probe： AIAA-1980-0358［R］. Reston： AIAA， 1980.
11	AHN H K， PARK C， SAWADA K. Dynamics of pyrolysis gas in charring materials ablation： AIAA-1998-0165［R］. Reston： AIAA， 1998.
12	OLYNICK D， CHEN Y K， TAUBER M E. Aerothermodynamics of the stardust sample return capsule［J］. Journal of Spacecraft and Rockets， 1999， 36（3）： 442-462.
13	MARVIN J G， AKIN C M. Combined effects of mass addition and nose bluntness on boundary-layer transition［J］. AIAA Journal， 1970， 8（5）： 857-863.
14	DEMETRIADES A， LADERMAN A J， VON SEGGERN L， et al. Effect of mass addition on the boundary layer of a hemisphere at Mach 6［J］. Journal of Spacecraft and Rockets， 1976， 13（8）： 508-509.
15	SCHNEIDER S P. Hypersonic boundary-layer transition with ablation and blowing［J］. Journal of Spacecraft and Rockets， 2010， 47（2）： 225-237.
16	周伟江，姜贵庆. 高超声速流中局部构件上质量引射的热防护特性研究［J］. 航空学报， 1999， 20（3）： 193-196.
	ZHOU W J， JIANG G Q. Study of heating protection features by mass injection over the local structure in a hypersonic flow［J］. Acta Aeronautica et Astronautica Sinica， 1999， 20（3）： 193-196 （in Chinese）.
17	肖雨，石义雷，粟斯尧. 质量引射对高超声速边界层影响研究［C］∥ 第十九届中国空气动力学物理气体动力学学术交流会.2019：124-126.
	XIAO Y， SHI Y L， SU S Y. Study of mass injection effects on hypersonic boundary layer［C］∥ 19th China Aerodynamics Physics Aerodynamics Academic Exchange Conference.2019：142-126 （in Chinese）.
18	沈斌贤，曾磊，刘骁，等. 高超声速飞行器主动质量引射热防护技术研究进展［J］. 空气动力学学报， 2022， 40（6）： 1-13.
	SHEN B X， ZENG L， LIU X， et al. Research progress of thermal protection technique by activemass injection for hypersonic vehicle［J］. Acta Aerodynamica Sinica， 2022， 40（6）： 1-13 （in Chinese）.
19	YOU Q， YANG X F， ZENG L， et al. Coupled heat transfer characteristics on chemically reacting interface of high-speed aircraft considering wall injection［C］∥ 32nd Congress of the International Council of the Aeronautical Sciences. 2021.
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 30000 K： NASA-RP-1232［R］. Washington， D.C.： NASA， 1990.
21	PARK C. Review of chemical-kinetic problems of future NASA missions， I： Earth entries［J］. Journal of Thermophysics and Heat Transfer， 1993， 7（3）： 385-398.
22	PARK C， HOWE J T， JAFFE R L， et al. Review of chemical-kinetic problems of future NASA missions， II： Mars entries［J］. Journal of Thermophysics and Heat Transfer， 1994， 8（1）： 9-23.
23	BAULCH D L， COBOS C J， COX R A， et al. Evaluated kinetic data for combustion modelling［J］. Journal of Physical and Chemical Reference Data， 1992， 21（3）： 411.
24	FUJITA K， YAMADAT T， ISHII N. Impacts of ablation gas kinetics on hyperbolic entry radiative heating［C］∥ 44th AIAA Aerospace Sciences Meeting. Reston： AIAA， 2006： 14357-14378.
25	COHEN N， WESTBERG K R. Chemical kinetic data sheets for high-temperature chemical reactions［J］. Journal of Physical and Chemical Reference Data， 1983， 12（3）： 531-590.
26	WARNATZ J. Rate coefficients in the C/H/O system［M］∥GARDINER W C， Jr. Combustion Chemistry. New York： Springer， 1984： 197-360.
27	COHEN N， WESTBERG K R. Evaluation and compilation of chemical kinetic data［J］. The Journal of Physical Chemistry， 1979， 83（1）： 46-50.
28	GNOFFO P A. Conservation equations and physical models for hypersonic air flows in thermal and chemical nonequilibrium［M］. Washington， D.C.： NASA， Office of Management， Scientific and Technical Information Division， 1989.
29	SARMA G S R. Physico-chemical modelling in hypersonic flow simulation［J］. Progress in Aerospace Sciences， 2000， 36（3/4）： 281-349.
30	MITCHELTREE R A， GNOFFO P A. Wake flow about a MESUR Mars entry vehicle： AIAA-1994-1958［R］. Reston： AIAA， 1994.
31	THOMPSON R A， GNOFFO P A. Implementation of a blowing boundary condition in the LAURA code： AIAA-2008-1243［R］. Reston： AIAA， 2008.
32	MARTIN A， BOYD I D. Modeling of heat transfer attenuation by ablative gases during the stardust reentry［J］. Journal of Thermophysics and Heat Transfer， 2015， 29（3）： 450-466.

反应序号	反应模型	M	C_f，_r / （cm³·（mol·s）^-1）	n_f，_r	E_f，_r /K
1	N₂+M⇔N+N+M	N₂， O₂， NO， CO， CO₂	7.0×10²¹	-1.6	113 200
2	N₂+M⇔N+N+M	N， O	3.0×10²²	-1.6	113 200
3	O₂+M⇔O+O+M	N₂， O₂， NO， CO， CO₂	2.0×10²¹	-1.5	59 500
4	O₂+M⇔O+O+M	N， O	1.0×10²²	-1.5	59 500
5	NO+M⇔N+O+M	N₂， O₂， NO， CO， CO₂	5.0×10¹⁵	0.0	75 500
6	NO+M⇔N+O+M	N， O	1.1×10¹⁷	0.0	75 500
7	CO₂+M⇔CO+O+M	N₂， O₂， NO， CO， CO₂	6.9×10²¹	-1.5	63 275
8	CO₂+M⇔CO+O+M	N， O	1.4×10²²	-1.5	63 275
9	H₂+M⇔H+H+M	N₂， O₂， NO， CO， CO₂， H₂， N， O	9.0×10¹⁴	0.0	48 400
10	H₂+M⇔H+H+M	H， H₂O	8.5×10¹⁹	-1.1	52 335
11	H₂O+M⇔OH+H+M	H， H₂O， N， O	1.3×10²¹	-1.0	60 000
12	N₂+O⇔NO+N		6.4×10¹⁷	-1.0	38 400
13	NO+O⇔O₂+N		8.4×10¹²	0.0	19 450
14	CO₂+O⇔CO+O₂		2.1×10¹³	0.0	27 800
15	CO+NO⇔CO₂+N		8.0×10⁶	0.88	13 300
16	H+CO₂⇔CO+OH		1.6×10¹⁴	0.0	13 200
17	H+H₂O⇔H₂+OH		1.0×10¹⁰	1.2	9 620
18	H+NO⇔N+OH		2.2×10¹⁴	0.0	24 900
19	H₂+O₂⇔OH+OH		2.5×10¹²	0.0	19 600
20	CH₄+CH₄+O₂⇒H₂+H₂+H₂+H₂+CO+CO		2.06×10¹⁴	0.0	24 358

组分	引射组分质量分数
组分	热解气体引射	空气引射
H₂O	0.66	0
CO₂	0.01	0
CO	0.04	0
CH₄	0.06	0
H₂	0.23	0
N₂	0	0.77
O₂	0	0.23

网格编号	网格分布（N_x ×N_y ）	Re_grid
网格1	245×112	40
网格2	347×159	4
网格3	491×225	2

攻角/（°）	0.005 kg/（m²·s）热解气体引射	0.005 kg/（m²·s）空气引射	0.01 kg/（m²·s）空气引射
0	0.90	0.63	0.92
5	0.75	0.49	0.81
9.5	0.63	0.38	0.66

攻角/（°）	0.005 kg/（m²·s）热解气体引射	0.005 kg/（m²·s）空气引射	0.01 kg/（m²·s）空气引射
0	0.95	0.72	0.96
5	0.87	0.58	0.88
9.5	0.77	0.45	0.75

Gas⁃injection effects on wall heat flux and skin⁃friction of vehicles

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