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

LIU Jiaqi; CHEN Rongqian; CHENG Jiaming

doi:10.13224/j.cnki.jasp.2019.11.009

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

更新时间：2026-07-07

- Numerical simulation of flow field under coaxial rigid rotor/fuselage interaction
- Vol. 34, Issue 11, Pages: 2377-2386(2019)
- 作者机构：
  
  厦门大学航空航天学院,福建,厦门,361102
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2019.11.009
  CLC：
- Published：2019
- 稿件说明：
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柳家齐, 陈荣钱, 程佳铭. 共轴刚性双旋翼/机身干扰流场数值模拟[J]. 航空动力学报, 2019, 34(11): 2377-2386.

doi: 10.13224/j.cnki.jasp.2019.11.009
柳家齐, 陈荣钱, 程佳铭. 共轴刚性双旋翼/机身干扰流场数值模拟[J]. 航空动力学报, 2019, 34(11): 2377-2386. DOI： 10.13224/j.cnki.jasp.2019.11.009.

doi: 10.13224/j.cnki.jasp.2019.11.009 DOI：

摘要

采用滑移网格技术求解Navier-Stokes (RANS)方程的方法

研究了共轴刚性双旋翼/机身的干扰问题。通过Caradonna-Tung旋翼、Robin直升机、Maryland直升机旋翼/机身干扰和Harrington 2共轴双旋翼等算例

验证了所提出的旋翼流场数值模拟方法的正确性。在此基础上

以Maryland机身为原型

分析了不同桨距的共轴刚性双旋翼与机身之间的干扰特性。结果表明:所提出的数值模拟方法能够很好地模拟共轴刚性双旋翼/机身的气动干扰特性;由于机身对于共轴刚性双旋翼下洗流场的阻滞作用

旋翼的悬停效率增加5%左右

并且随着拉力系数的增大使得悬停效率的增量更加明显;旋翼的悬停效率增加主要来源于下旋翼0°方位角附近的桨叶升力系数的增大

并且拉力系数的增量由桨根向桨尖方向逐渐减小。

Abstract

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.

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Related Institution

Department of Precision Instruments, School of Mechanical Engineering, Tsinghua University

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School of Mechanical and Materials Engineering, North China University of Technology

南京航空航天大学直升机旋翼动力学国家级重点实验室

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