基于表面压力信息的空间流向涡识别方法

doi:10.7527/S1000-6893.2023.27228

Abstract

Abstract:

The interaction between vortices and the object surface exists in various situations of aircraft. The vortices affect the pressure distribution on the surface and aerodynamic performance of the aircraft. The pressure distribution on the surface can reflect the spatial flow characteristics of the vortices around the aircraft. Combined with the angle of attack， sideslip angle and other flow parameters， the surface pressure distribution can predict the force state and motion trend of the aircraft. This study establishes a vortex signature identification method based on surface pressure distribution according to the theories of point vortex and “mirror vortex”. The experimental results demonstrate that the surface pressure distribution curve can characterize the spatial position （projection position and height of the vortex core distance surface） and intensity of the vortex. The correlation analysis between the spatial flow field measurement and the vortex identification result based on surface pressure distribution verifies the effectiveness of the proposed method. It has laid an important technical foundation for reconstructing the vortex flow structure around the aircraft and realizing the prediction of the aerodynamic forces of the aircraft.

Key words: vortex signature identification, vortex interaction, vortex intensity, vortex center position, correlation analysis

CLC Number:

V211.7

Jianglong GUO, Yunsong GU, Shuai LUO, Linkai LI. Spatial streamwise vortex signature identification based on surface pressure information[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(6): 127228-127228.

Figures/Tables 17

Fig. 1

Fig. 2

Fig. 3

Fig. 4

Fig. 5

Fig. 6

Fig. 7

Fig. 8

Table 1

Fig.9

Fig. 10

Fig. 11

Fig. 12

Fig. 13

Fig. 14

Table 2

Errors of vortex identification method based on surface pressure information （Re=3.21×105)

试验参数

展向位置误差/%

高度误差/%

强度误差/%

$x = 0.8 c, α = 12 °,$

$h = 0.3 c$

7.19

10.95

17.52

$x = 1.2 c, α = 8 °,$

$h = 0.3 c$

3.03

2.71

13.33

$x = 1.2 c, α = 8 °,$

$h = 0.2 c$

3.01

9.65

22.85

Table 2

Fig. 15

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测压孔截面弦向位置（x/c）	流向涡发展阶段
0.4	起始阶段
0.6	发展阶段
0.8	发展阶段
1.2	耗散阶段
1.4	耗散阶段

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Spatial streamwise vortex signature identification based on surface pressure information

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