Numerical simulation of flowfield of helicopter rotor and fuselage in forward flight based on unstructured embedded grid technique

YE Liang; ZHAO Qi-jun; XU Guo-hua

Chinese

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Numerical simulation of flowfield of helicopter rotor and fuselage in forward flight based on unstructured embedded grid technique

更新时间：2026-07-07

- Numerical simulation of flowfield of helicopter rotor and fuselage in forward flight based on unstructured embedded grid technique
- Vol. 24, Issue 4, (2009)
- 作者机构：
  
  南京航空航天大学直升机旋翼动力学国家级重点实验室,南京,210016
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2009
- 稿件说明：
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YE Liang, ZHAO Qi-jun, XU Guo-hua. Numerical simulation of flowfield of helicopter rotor and fuselage in forward flight based on unstructured embedded grid technique[J]. 2009, 24(4).
DOI：

YE Liang, ZHAO Qi-jun, XU Guo-hua. Numerical simulation of flowfield of helicopter rotor and fuselage in forward flight based on unstructured embedded grid technique[J]. 2009, 24(4). DOI：

摘要

建立了一个适用于前飞状态直升机单独旋翼、机身以及旋翼/机身组合体流场的数值计算方法及模型.在该方法中

使用非结构运动嵌套网格描述桨叶之间以及桨叶与机身之间的空间位置变化关系

控制方程采用惯性坐标系下的非定常Navier-Stokes(N-S)主控方程

空间方向上使用二阶迎风格式

时间方向上使用Lower-upper symmetric Gauss-Seidel(LU-SGS)格式.对于求解中遇到的旋翼/机身间距离过近所导致的贡献单元生成困难问题提出了一种新的解决方法.应用所建立的方法

分别对单独旋翼、机身及旋翼机身组合体的前飞绕流场进行了数值模拟与分析

计算结果与试验结果的对比表明本文建立的方法对直升机的前飞绕流场的计算和分析是很有效的.

Abstract

A numerical method has been developed to simulate the flowfield of the helicopter rotor

fuselage and the combination of them in forward flight.In this method

unstructured embedded grid technique was used to simulate the position transformation relationship between the rotor and its fuselage

the three-dimensional unsteady Navier-Stokes(N-S) equations were discretized by a second-order upwind finite-volume scheme and the lower-upper symmetric Gauss-Seidel(LU-SGS) scheme was employed in time-stepping.A new method was given to solve the problem of the "donor searching" when the space between the rotor and its fuselage was too narrow.Based on this model

the flowfield of the single rotor

fuselage and the combination of them were calculated

the comparisons of the calculated results with the experimental data indicate that the present method is very effective to analyze the helicopter flowfield in forward flight.

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Related Institution

National Laboratory of Science and Technology on Rotorcraft Aeromechanics, Nanjing University of Aeronautics and Astronautics

China Helicopter Research and Development Institute, Aviation Industry Corporation of China, Limited

南京航空航天大学直升机旋翼动力学国家级重点实验室

National Key Laboratory of Science and Technology on Rotorcraft Aeromechanics, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics

School of Naval Architecture and Ocean Engineering, Jiangsu University of Science and Technology

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