尖锥高速边界层转捩动态气动特性测量及分析

doi:10.7527/S1000-6893.2024.31430

Abstract

Abstract:

In high-speed flows， boundary layer transition will not only significantly increase heat-flux and affect the thermal protection design， but also change aerodynamic load on aircraft surface， and then change static/dynamic stability. This will have an impact on the flight safety and control characteristics of aircraft， so transition is one of the important aerodynamic issues in high-performance aerodynamic design. In the present study， the test of forced vibration dynamic derivative measurement is carried out in a ∅ 1 m conventional high-speed wind tunnel with a 7° half-angle sharp cone at Mach number 6， and the infrared thermogram is measured simultaneously. Not only the static/dynamic derivatives of pitching moment at different Reynolds numbers and angles of attack， but also a series of clear transition front are obtained. By comparing them， the relationship between static/dynamic stability and transition position is analyzed， and the mechanism of change of aerodynamic moment characteristics is analyzed by steady numerical simulation of typical transition flow. The study makes up for the deficiency of previous research methods， and further clarifies the relationship and physical mechanism between transition and dynamic aerodynamic characteristics. The results show that the influence of transition on dynamic aerodynamic characteristics is closely related to the position of the transition region relative to the center of mass， and the static/dynamic stability will change significantly when the transition front is in the downstream region of the center of mass. The asymmetric change of wall pressure and friction caused by transition is the fundamental reason for the change of static/dynamic stability， and friction plays an equal role as pressure in the additional moment induced by transition.

Key words: high-speed flow, boundary layer, transition, aerodynamic stability, wind tunnel test

CLC Number:

V211.3

Yifeng ZHANG, Xinguang WANG, Leitao GUO, Yang XU, Qi CHEN. Measurement and analysis of influence of high-speed boundary layer transition on dynamic aerodynamic characteristics of sharp cone[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(12): 131430.

Figures/Tables 21

Fig.1

Fig.2

Fig.3

Table 1

Table 2

Aerodynamic derivative （repetitive test）

试验序号	Ma	Re_∞ /（10⁷ m^-1）	α/（°）	C_ma	$C m a ˙$ +C_mq
No.230374	6	1.0	2	-0.255 7	-3.959 2
No.230391	6	1.0	2	-0.259 8	-3.400 7

Table 2

Fig.4

Table 3

Aerodynamic derivative （frequency variation）

Ma	Re_∞ /（10⁷m^-1）	α /（°）	f /Hz	C_ma	$C m a ˙$ +C_mq
6	1.0	4	2	-0.238 5	-4.327 3
6	1.0	4	4	-0.258 2	-4.303 5
6	1.0	4	8	-0.267 2	-4.277 9

Table 3

Fig.5

Fig.6

Fig.7

Fig.8

Table 4

Aerodynamic derivative （Reynolds number variation）

Ma	Re_∞ /（10⁷ m^-1）	C_ma /rad^-1	$C m a ˙ + C m q$ /rad^-1
6	0.4	-0.247 2	-3.656 2
6	0.8	0.031 3	-7.581 6
6	1.0	-0.032 3	-6.334 4
6	1.2	-0.271 6	-3.127 1
6	1.4	-0.314 4	-2.023 2
6	2.0	-0.293 3	-2.941 6
6	2.5	-0.267 5	-2.893 6
6	3.0	-0.252 9	-3.254 6

Table 4

Fig.9

Fig.10

Fig.11

Fig.12

Table 5

Aerodynamic derivatives （attack angle variation）

Ma	α/（°）	C_ma /rad^-1	$C m a ˙$ +C_mq /rad^-1
6	0	-0.314 4	-2.023 2
6	1	-0.305 5	-2.837 2
6	2	-0.240 6	-4.451 1
6	3	-0.222 0	-4.866 2
6	4	-0.234 1	-5.037 9
6	6	-0.249 1	-5.029 0

Table 5

Fig.13

Fig.14

Fig.15

Table 6

References 23

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项目	Ma	Re_∞ /（10⁷ m^-1）	α/（°）	f/Hz	K	研究内容
1	6	1.45	0	2~8	0.001 96~0.007 86	频率影响
2	6	0.50~3.00	0	2	0.001 96	雷诺数影响
3	6	1.50	0~6	2	0.001 96	攻角影响

状态	C_m /10^-2	C_mp /10^-2	C_m_vis/10^-2	无黏占比/%	黏性占比/%
层流	0.639 8	0.620 1	0.019 7	97	3
转捩	0.557 3	0.580 9	-0.023 5	104	-4
差量	-0.082 5	-0.039 2	-0.043 2	48	52

Measurement and analysis of influence of high-speed boundary layer transition on dynamic aerodynamic characteristics of sharp cone

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