旋翼翼型气动设计与验证方法

张卫国; 孙俊峰; 招启军; 武杰; 李国强; 马帅; 吴霖鑫

doi:10.7638/kqdlxxb-2021.0315

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旋翼翼型气动设计与验证方法

翼型研究新进展 | 更新时间：2026-05-28

- 旋翼翼型气动设计与验证方法
- Aerodynamic design and verification methods of rotor airfoils
- 空气动力学学报 2021年39卷第6期页码：136-148
- 作者机构：
  
  1. 西北工业大学航空学院,西安,710000
  2. 中国空气动力研究与发展中心低速空气动力研究所,绵阳,621000
  3. 中国空气动力研究与发展中心计算空气动力研究所,绵阳,621000
  4. 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
  5. 国防科技大学空天科学学院,长沙,410073
- 作者简介：
  
  张卫国（1975-），男，山东兖州人，研究员，研究方向：直升机空气动力学. E-mail：zwglxy@163.com
  孙俊峰*，高级工程师，研究方向：直升机空气动力学. E-mail: jfsun3@163.com
- 基金信息：
  
  装备预先研究项目（41406040202，30103010304）;基础和前沿技术研究基金（PJD20190002）;风雷青年创新基金（PJD20190003）
- DOI：10.7638/kqdlxxb-2021.0315
  中图分类号： V211.52
- 纸质出版：2021
- 稿件说明：
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张卫国, 孙俊峰, 招启军, 等. 旋翼翼型气动设计与验证方法[J]. 空气动力学学报, 2021, 39(6): 136−148, 155.

ZHANG Weiguo, SUN Junfeng, ZHAO Qijun, et al. Aerodynamic design and verification methods of rotor airfoils[J]. 2021, 39(6): 136-148.
张卫国, 孙俊峰, 招启军, 等. 旋翼翼型气动设计与验证方法[J]. 空气动力学学报, 2021, 39(6): 136−148, 155. DOI： 10.7638/kqdlxxb-2021.0315

ZHANG Weiguo, SUN Junfeng, ZHAO Qijun, et al. Aerodynamic design and verification methods of rotor airfoils[J]. 2021, 39(6): 136-148. DOI： 10.7638/kqdlxxb-2021.0315.

摘要

为满足我国直升机研发对自主旋翼翼型的迫切需求，开展了旋翼翼型气动优化设计与验证方法研究。发展了旋翼翼型指标分析与给定方法，给出了我国直升机旋翼翼型谱系规划设想，以进化多目标算法为基础结合PCA算法建立了旋翼翼型多点/多目标优化设计方法，突破了旋翼翼型气动特性精准测量风洞试验技术。利用所建立的方法对典型厚度翼型进行了优化设计并开展了风洞试验验证，计算评估与试验验证均表明自主设计翼型综合性能较国外参考翼型有一定提升。在此基础上，进一步构建了旋翼性能理论计算与试验验证综合评估方法，两种方式得到的旋翼主要性能数据偏差小于5%，表明该方法具有较高的可靠性。评估结果显示，基于设计翼型的旋翼模型气动性能较基于参考翼型的旋翼模型提升了3%。

Abstract

In order to meet the urgent needs of next-generation helicopters for independent-designed high-performance rotor airfoils

a study on the aerodynamic optimization design and verification method of rotor airfoils has been carried out. The analyze and setting methods of rotor airfoil performance indicators are developed

and the helicopter rotor airfoil pedigree planning is proposed as well. Based on the evolutionary multi-objective algorithm combined with the principal component analysis (PCA) algorithm

a multi-point/multi-objective optimization design method for rotor airfoils is established. The method is then used to optimize the design of airfoils with typical thicknesses. Aerodynamic performance of the optimized airfoils are verified by wind-tunnel experiments in which breakthrough in the accurate measurement of rotor airfoil aerodynamic characteristics has been achieved. Both computational and experimental results show that the comprehensive performance of the designed airfoil has an improvement to some extent compared with the reference one. On this basis

a comprehensive evaluation method for theoretical calculation and experimental verification of rotor performance is constructed. The deviation of the main performance indicators of the rotor obtained by the two methods is less than 5%

indicating that the method is highly reliable. The evaluation results show that the aerodynamic performance of the rotor model based on the designed airfoil is improved by 3% compared with the one based on the reference airfoil.

关键词

Keywords

references

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