一种适用于流固耦合模拟的高精度气动载荷传递方法

doi:10.7527/S1000-6893.2025.31425

Abstract

Abstract:

In numerical simulations of fluid-solid coupling based on partitioned method， the fluid and solid solvers utilize independent grids for computations， so the grids are typically non-matching at the coupling interface. Physical quantities such as aerodynamic forces need to be transferred at the interface， and their conservation is essential to the accuracy of the simulation solutions. To reduce the error of aerodynamic force transfer， this paper proposes a data transfer method based on local surface degradation and accurate cell integration. In this method， a generalized two-dimensional coordinate system is initially constructed based on the solid mesh. Subsequently， the fluid mesh is projected， and the intersection area is calculated to determine the contribution of the fluid cells to the solid nodal force. The method has been demonstrated to be effective in achieving accurate and efficient data transfer between non-matching meshes of varying types. Compared to the traditional method， the proposed method can essentially ensure the comprehensive conservation of force， facilitate near-zero error aerodynamic force transfer， and result in a smoother aerodynamic force distribution. Additionally， the error of the momentum can be reduced by more than one order of magnitude. Finally， the influence of different data transfer methods on the fluid-solid coupling results are evaluated through the simulations of Rotor67， STCF4 standard turbine and Hirenasd wing which indicate that the interface data transfer approach proposed in this paper is more precise in calculations of solid deformation and aerodynamic damping.

Key words: fluid-solid coupling, non-matching mesh, data transfer, aerodynamic force conservation, cell integral

CLC Number:

Zhongyu DU, Pengcheng DU, Fangfei NING. A high-precision aerodynamic load transfer method for fluid-solid coupling simulation[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(12): 131425.

Figures/Tables 42

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Table 1

Comparison of force and momentum in solid side by different methods （Rotor67， FEM mesh 1）

参数	CFD	QP	Error of QP/%	RBF	Error of RBF/%	CI	Error of CI/%
$F x / N$	-299.80	-300.20	0.134	-304.46	1.55	-299.80	0
$F y / N$	210.66	211.84	0.559	212.45	0.850	210.66	0
$F z / N$	-38.160	-38.634	1.24	-39.589	3.74	-38.160	0
$M x / (N · m)$	38.104	38.246	0.371	38.387	0.743	38.089	-0.038 9
$M y / (N · m)$	-62.344	-62.389	0.072 9	-63.072	1.17	-62.315	-0.046 6
$M z / (N · m)$	-0.386 27	-0.370 54	-4.07	-0.680 96	76.3	-0.385 71	-0.146

Table 1

Table 2

Comparison of force and momentum in solid side by different methods （Rotor67， FEM mesh 2）

参数	CFD	QP	Error of QP/%	RBF	Error of RBF/%	CI	Error of CI/%
$F x / N$	-299.80	-299.41	-0.131	-299.36	-0.146	-299.80	0
$F y / N$	210.66	210.19	-0.222	209.34	-0.625	210.66	0
$F z / N$	-38.160	-37.926	-0.613	-37.424	-1.93	-38.160	0
$M x / (N · m)$	38.104	38.035	-0.182	37.932	-0.451	38.097	-0.018 1
$M y / (N · m)$	-62.344	-62.266	-0.141	-62.161	-0.293	-62.333	-0.016 6
$M z / (N · m)$	-0.386 27	-0.402 93	4.31	-0.635 26	64.5	-0.385 55	-0.186

Table 2

Table 3

Fig.17

Fig.18

Fig.19

Table 4

Comparison of force and momentum in solid side by different methods （STCF4）

参数	CFD	QP	Error of QP/%	RBF	Error of RBF/%	CI	Error of CI/%
$F x / N$	118.97	119.26	0.243	118.84	-0.111	118.97	0
$F y / N$	59.166	59.103	-0.108	58.758	-0.646	59.167	0
$F z / N$	0.039 220	0.038 948	-0.693	0.035 064	-10.6	0.039 220	0
$M x / (N · m)$	10.572	10.557	-0.141	10.503	-0.651	10.572	0.001 00
$M y / (N · m)$	21.218	21.268	0.237	21.197	-0.097 6	21.218	0.001 00
$M z / (N · m)$	-7.052 1	-7.067 1	0.212	-7.030 7	-0.304	-7.052 7	0.008 25

Table 4

Fig.20

Fig.21

Fig.22

Table 5

Comparison of force and momentum in solid side by different methods （Hirenasd wing）

参数	CFD	QP	Error of QP/%	RBF	Error of RBF/%	CI	Error of CI/%
$F x / N$	102.70	754.75	635	805.12	684	102.70	0
$F y / N$	-2 299.3	-2 736.4	19.0	-2 767.7	20.4	-2 299.3	0
$F z / N$	5 710.1	5 877.5	2.93	6 119.5	7.17	5 710.1	0
$M x / (N · m)$	3 331.9	3 368.2	1.09	3 553.0	6.64	3 332.0	0.003 14
$M y / (N · m)$	3 083.9	3 155.7	2.33	3 345.5	8.48	3 084.7	0.025 9
$M z / (N · m)$	-486.92	-654.47	34.4	-655.87	34.7	-487.5	0.119

Table 5

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Table 6

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Table 7

Lift and drag coefficients of Hirenasd wing

参数	QP	RBF	CI	文献［40］
$C L$	0.333 3	0.332 6	0.334 2	0.336 6
$C D$	0.014 7	0.014 8	0.014 7	0.014 7

Table 7

Fig.35

References 40

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算例	CPU时间/s
算例	QP	RBF	CI
网格1	4.84	3.75	0.76
网格2	127.07	49.41	14.32

模态	固有频率/Hz
模态	本文	文献［39］
1	26.5	26.5
2	86.0	86.0
3	157.0	156.9
4	189.5	189.3
5	272.9	272.9
6	322.2	321.8

A high-precision aerodynamic load transfer method for fluid-solid coupling simulation

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