An indicator design method of advancing blade concept rotor airfoil based on X2TD aircraft

ZHANG Wei; HU Ou; WANG Fei; ZHAO Qijun

doi:10.7638/kqdlxxb-2021.0170

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An indicator design method of advancing blade concept rotor airfoil based on X2TD aircraft

更新时间：2026-05-28

- An indicator design method of advancing blade concept rotor airfoil based on X2TD aircraft
- Vol. 40, Issue 6, Pages: 73-82(2022)
- 作者机构：
  
  1. 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
  2. 中国直升机设计研究所,景德镇,333001
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2021.0170
  CLC： V211.52
- Published：2022
- 稿件说明：
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张威, 胡偶, 王菲, 等. 基于X2TD高速直升机的前行桨叶概念旋翼翼型指标设计方法[J]. 空气动力学学报, 2022, 40(6): 73−82.

ZHANG Wei, HU Ou, WANG Fei, et al. An indicator design method of advancing blade concept rotor airfoil based on X2TD aircraft[J]. 2022, 40(6): 73-82.
张威, 胡偶, 王菲, 等. 基于X2TD高速直升机的前行桨叶概念旋翼翼型指标设计方法[J]. 空气动力学学报, 2022, 40(6): 73−82. DOI： 10.7638/kqdlxxb-2021.0170

ZHANG Wei, HU Ou, WANG Fei, et al. An indicator design method of advancing blade concept rotor airfoil based on X2TD aircraft[J]. 2022, 40(6): 73-82. DOI： 10.7638/kqdlxxb-2021.0170.

摘要

为准确模拟高速旋翼机桨叶剖面气动特性，发展了基于CFD/CAMRAD Ⅱ耦合算法的直升机旋翼翼型工作环境分析方法，并对方法进行了验证。在此基础上针对直升机旋翼桨叶变迎角、变马赫数的工作特点，构建了基于“

平面升阻比等高线”的全方位/全剖面旋翼翼型指标设计方法。从研究前行桨叶概念旋翼大反流、强径向流、强压缩性流场特点和升力偏置、变转速工作方式入手，针对X2TD直升机高速飞行状态下上/下旋翼、前/后行侧桨叶翼型剖面的气动特征，有针对性地提出旋翼翼型选择标准或设计、改进方向，并与国外设计结果进行了对比分析，得到了一些有意义的结论。所建立的翼型指标设计方法和计算分析结果可为高速直升机旋翼气动设计的深入研究提供参考。

Abstract

In order to simulate the aerodynamic characteristics of high speed helicopter blade sections

an operating condition analysis method for helicopter rotor airfoil is developed and verified based on the CFD and CAMRAD Ⅱ method.

And an airfoil indicator design method

named “

plane lift-drag ration contour”

is constructed

taking into account of the characteristics of Mach number and angle of attack of a rotating blade. The method is suitable for the airfoil indicator design in full azimuth and full span blade sections

and is used to analyze the Advancing Blade Concept rotor airfoils. Based on the study of ABC rotor f

low field characteristics of large reverse flow field

strong radial flow

strong compressible flow

lift offset and variable rotation speed as well as the further analysis of the aerodynamic characteristics of advancing and retreating side blade airfoil section for both upper and lower rotors

the improvement of airfoil selection criteria and design indicator have been done. The computational results are in good agreements with the reference results. The airfoil indicator design method and computational results are useful for the intensively studying of ABC rotor aerodynamic design.

关键词

Keywords

references

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