高速飞行器质量引射条件下气动热数值计算

doi:10.7527/S1000-6893.2026.32462

Abstract

Abstract:

Proper understanding and evaluation of the aerothermal environment with mass injection for high-speed aircraft are prerequisites to develop corresponding thermal protection technology. To address the prediction of aerothermal environment with mass injection， the numerical simulation method of mass injection is proposed and verified in high-temperature nonequilibrium flow. Subsequently， a modified heat flux characterization formula is theoretically derived considering comprehensive wall effects， including catalysis， ablation， pyrolysis and active injection. The new characterization method and heat reduction mechanisms are numerically investigated using a blunt wedge configuration in typical flight states. The results demonstrate the following： using the heat flux ultimately experienced by the vehicle structure as the criterion for wall heat flux assessment aligns with traditional wall heat flux formula while also providing a reasonable evaluation of heat flux with complex wall effects. Conventional heat flux formula needs to be corrected since it overestimates wall heat flux and underestimates cooling efficiency when evaluating the thermal reduction effect of mass injection. The corrected heat flux expression under mass injection conditions includes heat conduction from flow field， heat absorption/release from wall reactions， and formation enthalpy of injected media， degenerating into the traditional heat flux expression in non-ablative and non-injection conditions. For non-catalytic， non-ablative and active injection wall， heat flux consists solely of conductive heat flux. As a result， cooling effect of active injection is achieved by significantly reducing the normal temperature gradient at the wall. The cooling efficiency is further improved while incorporating the enthalpy of injected water vapor， but the dominant factor remains the reduction of conductive heat flux.

Key words: mass injection, aerothermal, nonequilibrium, catalysis, ablation, high-speed aircraft

CLC Number:

V411.3

Qingzong LIU, Mingsong DING, Weizhong DONG, Wenhui KONG, Tao JIANG. Numerical computation on aerothermal environment with mass injection for high-speed aircraft[J]. Acta Aeronautica et Astronautica Sinica, 2026, 47(5): 132462.

Figures/Tables 37

Table 1

Table 2

Physical-chemical data

物质	M_i / （g·mol^-1）	θ_V，_m /K	g_i_，_m	g₀_，i	g₁_，i	θ_e_i /K	∆h $i 0$ /（10⁵J·mol^-1）
N₂	28	3 395	1	1	3	72 250	0
O₂	32	2 239	1	3	2	11 390	0
NO	30	2 817	1	4	8	55 850	0.913
CO₂	44	1 903 945 3 329	1 2 1	1 1 1	2 2 2	66 200 66 200 66 200	-3.94 -3.94 -3.94
C₂	24	2 362	1	6	6	27 800	8.30
CO	28	3 074	1	1	6	70 060	-1.11
CN	26	2 976	1	2	4	13 300	4.39
H₂O	18	2 295 5 264 5 404	1 1 1	2 2 2	2 2 2	77 420 77 420 77 420	-2.42 -2.42 -2.42
H₂	2	6 326	1	1	1	131 940	0
OH	17	5 375	1	4	2	47 030	0.373
C	12	0	1	9	5	14 670	7.17
H	1	0	1	2	6	118 370	2.18
N	14	0	1	4	10	27 670	4.73
O	16	0	1	9	5	22 850	2.49

Table 2

Fig.1

Fig.2

Fig.3

Fig.4

Fig.5

Fig.6

Fig.7

Fig.8

Table 3

Table 4

Fig.9

Table 5

Fig.10

Fig.11

Fig.12

Fig.13

Fig.14

Fig.15

Fig.16

Fig.17

Fig.18

Fig.19

Fig.20

Fig.21

Fig.22

Fig.23

Fig.24

Fig.25

Table 6

Fig.26

Fig.27

Fig.28

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Fig.30

Fig.31

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序号	反应模型	序号	反应模型
1	N₂+M=N+N+M	16	CO+C=C₂+O
2	O₂+M=O+O+M	17	C+N₂=CN+N
3	NO+M=N+O+M	18	CN+C=C₂+N
4	CO₂+M=CO+O+M	19	CO+N=CN+O
5	C₂+M=C+C+M	20	CO+N=C+NO
6	CO+M=C+O+M	21	CO+CO=CO₂+C
7	CN+M=C+N+M	22	CO+CO=C₂+O₂
8	H₂O+M=H+OH+M	23	NO+CO=CO₂+N
9	H₂+M=H+H+M	24	N₂+O₂=NO+NO
10	OH+M=O+H+M	25	CO+OH=CO₂+H
11	NO+O=N+O₂	26	H₂+OH=H₂O+H
12	N₂+O=NO+N	27	H+O₂=OH+O
13	CO+O=O₂+C	28	H₂+O=OH+H
14	CN+O=NO+C	29	OH+OH=H₂O+O
15	CO₂+O=O₂+CO

Case	计算模型	特殊效应区域壁面条件
1	完全气体	无引射
2	完全气体	空气引射
3	真实气体	非催化、无引射
4	真实气体	非催化、二氧化碳引射
5	真实气体	非催化、空气引射
6	真实气体	非催化、水蒸气引射
7	真实气体	非催化、热解气体引射
8	真实气体	空气有限催化、无引射
9	真实气体	空气有限催化、水蒸气引射
10	真实气体	碳碳材料烧蚀、无主动引射
11	真实气体	碳碳材料烧蚀、水蒸气引射

参数	引射工质	CO₂	Air	H₂O	Gas
组分质量占比	CO₂	1	0	0	0.010 6
	N₂	0	0.77	0	0
	O₂	0	0.23	0	0
	H₂O	0	0	1	0.702 1
	CO	0	0	0	0.042 6
	H₂	0	0	0	0.244 7
摩尔质量/（g·mol^-1）		44.00	28.83	18.00	6.13
引射总焓/（10⁶J·kg^-1）		-7.34	1.64	-1.06	-2.17

网格	N_x ×N_y	∆x/mm	Re_Grid
Grid 1	201×56	0.20~0.67	17.00~55.00
Grid 2	381×91	0.02~0.10	1.70~8.30
Grid 3	381×96	0.01~0.05	0.83~4.10

序号	引射量/（g·m^-2·s^-1）	壁温/K	液态水温升生成焓/（kW·m^-2）	汽化相变生成焓/（kW·m^-2）	水蒸气温升生成焓/（kW·m^-2）
1	1	1 500	-0.31	-2.27	-2.37
2	5	1 500	-1.57	-11.35	-11.83
3	10	1 500	-3.14	-22.70	-23.66
4	10	1 000	-3.14	-22.70	-13.16
5	10	500	-3.14	-22.70	-2.66

Numerical computation on aerothermal environment with mass injection for high-speed aircraft

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