Numerical simulation of flow field under coaxial rigid rotor/fuselage interaction

被引：0

作者：

Liu J. ^{[1
]}

Chen R. ^{[1
]}

Cheng J. ^{[1
]}

Lin W. ^{[1
]}

You Y. ^{[1
]}

机构：

[1] School of Aerospace Engineering, Xiamen University, Xiamen, 361102, Fujian

来源：

Hangkong Dongli Xuebao/Journal of Aerospace Power | 2019年 / 34卷 / 11期

关键词：

Aerodynamic interaction; Coaxial rigid rotor; High speed helicopter; Rotor/fuselage interaction; Sliding mesh;

D O I：

10.13224/j.cnki.jasp.2019.11.009

中图分类号：

学科分类号：

摘要：

The method of solving the Navier-Stokes (RANS) equation by the sliding mesh technique was studied, and the interaction problem of the coaxial rigid rotor/fuselage was analyzed. The correctness of the numerical simulation of the flow field related to rotor was verified by the examples of Caradonna-Tung rotor, Robin helicopter, Maryland helicopter rotor/fuselage interaction, and Harrington 2 coaxial rotors. On this basis, with the Maryland fuselage as the model prototype, the interference characteristics between the coaxial rigid rotor with different pitches and the fuselage were analyzed. Results showed that numerical simulation method can simulate the aerodynamic interference characteristics of the coaxial rigid rotor/fuselage very well; the hovering efficiency of the rotor increased by about 5% due to the blockage of the airflow field of the coaxial rigid rotor., and the increase of the hovering efficiency was more obvious with the increase of the pulling coefficient; the increase of the hovering efficiency of the rotor was mainly related to the increase of the blade lift coefficient near the 0° azimuth of the lower rotor, and the increment of the tensile coefficient was gradually reduced from the root of the blade to the tip of the blade. © 2019, Editorial Department of Journal of Aerospace Power. All right reserved.

引用

页码：2377 / 2386

页数：9

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