临近空间高速飞行器微量气动力试验及计算

doi:10.7527/S1000-6893.2022.27072

Abstract

Abstract:

Structural design and static calibration were developed for accurate measurement of micro aerodynamic wind tunnel tests in near space atmospheric environments. Then，the simple blunt cone model was used for the micro-aerodynamic force experiment verification，and the complex shape of the triangular lift body was adopted to explore the ability to measure the micro-aerodynamic force in thinner atmospheric environments. The results show that the repeatability accuracy of aerodynamic data of each balance load unit is better than 4.8% in the three times of the blunt cone shape verification test. In the exploration test，the triangular lift body adopts the lowest density state the wind tunnel can currently achieve，and the test results show that the micro-force balance performs well in the limit state. The numerical simulation results，compared with the experimental results，show that the aerodynamic forces of the blunt cone and the delta wing lift body are in good agreement with those measured by microbalance； for the simple blunt cone，the compressive resistance of the blunt surface is significantly higher than the frictional resistance under its test conditions，while the surface friction ratio of the complex delta wing body is equal to the piezoresistive，with much thinner test conditions.

Key words: near space, wind tunnel test, microbalance, aerodynamic force, high speed vehicles

CLC Number:

V411.3

Junhong LI, Xuhong JIN, Chunfeng LIU, Wenbo MIAO, Xiaoli CHENG. Microaerodynamic experiment and computation of near space high speed vehicles[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(6): 127072-127072.

Figures/Tables 25

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References 24

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工况	Ma	P₀/Pa	q/Pa	T₀/°C	Re/m^-1
1	8.014	1 216 384	5 538.1	291.7	4 322 697
2	8.014	1 219 124	5 550.6	327.4	3 897 376
3	8.014	1 219 881	5 554.0	331.3	3 856 281

工况	α/（°）	C_N	C_A	C_mz
1	-4	-0.092 34	0.177 85	0.057 45
	-2	-0.045 18	0.174 95	0.027 91
	0	-0.001 78	0.172 86	0.001 22
	2	0.043 69	0.174 81	-0.026 91
	4	0.095 82	0.182 53	-0.059 61
2	-4	-0.097 85	0.185 952	0.062 50
	-2	-0.047 19	0.180 981	0.030 14
	0	-0.000 73	0.178 416	0.000 51
	2	0.046 34	0.180 368	-0.029 50
	4	0.099 53	0.186 346	-0.063 70
3	-4	-0.098 36	0.185 31	0.061 98
	-2	-0.047 81	0.182 38	0.030 13
	0	-0.000 65	0.181 59	0.000 39
	2	0.046 87	0.183 91	-0.029 23
	4	0.100 03	0.187 78	-0.063 50

a/（°）	标准偏差S/%
a/（°）	C_N	C_A
-4	3.6	2.3
-2	1.6	4.0
0	0.7	4.6
2	1.9	4.8
4	2.5	1.7

α/（°）	C_N	C_A	C_mz
0	-0.267 09	0.338 78	0.200 56
2	-0.025 49	0.321 24	0.039 19
4	0.195 55	0.270 07	-0.113 04
6	0.352 90	0.236 15	-0.220 24

α/（°）	P_cx	P_cy	f_cx	f_cy
-4	0.142 43	-0.084 40	0.025 30	-0.003 18
-2	0.139 22	-0.040 10	0.024 40	-0.001 56
0	0.138 26	0	0.024 10	0
2	0.139 23	0.040 20	0.024 40	0.001 56
4	0.142 45	0.084 50	0.025 30	0.003 19

Microaerodynamic experiment and computation of near space high speed vehicles

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α/（°）	P_cx	P_cy	f_cx	f_cy
0	0.068 9	-0.225 51	0.233 931	-0.045
2	0.052 5	-0.084 5	0.219 908	0.025 9
4	0.044 2	0.039 7	0.210 442	0.097 7
6	0.053 2	0.303 829	0.199 762	0.041 9

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