TY - JOUR
T1 - 基于 CFD / CAA 耦合边界方法的翼型尾缘噪声预测
AU - Lu, Rui
AU - Ding, Yongle
AU - Yu, Peixun
AU - Tan, Kun
AU - Pan, Guang
N1 - Publisher Copyright:
©2023 Journal of Northwestern Polytechnical University.
PY - 2023/4
Y1 - 2023/4
N2 - Flow⁃induced noise hybrid prediction method based on sound wave boundary condition is an effective numerical method to deal with a flow⁃induced noise problems of complex configuration. This method can not only finely simulate the sound source, but also analyze the noise propagation characteristics. In this paper, numerical methods such as space⁃time discrete scheme and boundary conditions involved in discrete solution of acoustic perturbation equations(APE) are developed, and strategies such as adding buffer layer are proposed to improve divergence caused by numerical discontinuity at the junction of sound source region and propagation region, so as to establish a high⁃precision flow⁃induced noise hybrid method. In order to study the rationality of flow⁃induced noise hybrid method, the numerical simulation of acoustic radiation at the trailing edge of NACA0012 airfoil in BANC experiment was carried out. Compared with the results of sound field solved by large eddy simulation method, the analysis shows that the high⁃precision flow⁃induced noise hybrid method based on sound wave boundary conditions can predict the spatial sound field distribution with high precision and directly reflect the interaction between sound waves. Compared with the results of large eddy simulation, the error of sound pressure level is less than 2 dB, and the noise directional distribution trend is consistent.
AB - Flow⁃induced noise hybrid prediction method based on sound wave boundary condition is an effective numerical method to deal with a flow⁃induced noise problems of complex configuration. This method can not only finely simulate the sound source, but also analyze the noise propagation characteristics. In this paper, numerical methods such as space⁃time discrete scheme and boundary conditions involved in discrete solution of acoustic perturbation equations(APE) are developed, and strategies such as adding buffer layer are proposed to improve divergence caused by numerical discontinuity at the junction of sound source region and propagation region, so as to establish a high⁃precision flow⁃induced noise hybrid method. In order to study the rationality of flow⁃induced noise hybrid method, the numerical simulation of acoustic radiation at the trailing edge of NACA0012 airfoil in BANC experiment was carried out. Compared with the results of sound field solved by large eddy simulation method, the analysis shows that the high⁃precision flow⁃induced noise hybrid method based on sound wave boundary conditions can predict the spatial sound field distribution with high precision and directly reflect the interaction between sound waves. Compared with the results of large eddy simulation, the error of sound pressure level is less than 2 dB, and the noise directional distribution trend is consistent.
KW - acoustic perturbation equations
KW - flow⁃induced noise
KW - large eddy simulation
KW - sound wave boundary condition
KW - trailing edge noise
UR - http://www.scopus.com/inward/record.url?scp=85162169747&partnerID=8YFLogxK
U2 - 10.1051/jnwpu/20234120319
DO - 10.1051/jnwpu/20234120319
M3 - 文章
AN - SCOPUS:85162169747
SN - 1000-2758
VL - 41
SP - 319
EP - 328
JO - Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University
JF - Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University
IS - 2
ER -