高空长航时无人机螺旋桨后掠桨叶气动研究

马成宇; 何国毅; 王琦

doi:10.7638/kqdlxxb-2017.0144

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高空长航时无人机螺旋桨后掠桨叶气动研究

研究论文 | 更新时间：2026-05-28

- 高空长航时无人机螺旋桨后掠桨叶气动研究
- Aerodynamic performance study on backswept blade of HALE UAV propeller
- 空气动力学学报 2019年37卷第5期页码：795-803
- 作者机构：
  
  南昌航空大学飞行器工程学院,南昌,330063
- 作者简介：
  
  马成宇(1990-), 男, 河北石家庄人, 硕士研究生, 研究方向:飞行器设计.E-mail:imachengyu@126.com
  何国毅(1968-), 男, 博士, 副教授.E-mail:hegy509@163.com
- 基金信息：
  
  国家自然科学基金（11462015）;江西省自然科学基金（20142BAB206026）;江西省科技厅重点研发计划（20151BBE50026）
- DOI：10.7638/kqdlxxb-2017.0144
  中图分类号： V211.44
- 纸质出版：2019
- 稿件说明：
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马成宇, 何国毅, 王琦. 高空长航时无人机螺旋桨后掠桨叶气动研究[J]. 空气动力学学报, 2019, 37(5): 795-803.

MA Chengyu, HE Guoyi, WANG Qi. Aerodynamic performance study on backswept blade of HALE UAV propeller[J]. 2019, 37(5): 795-803.
马成宇, 何国毅, 王琦. 高空长航时无人机螺旋桨后掠桨叶气动研究[J]. 空气动力学学报, 2019, 37(5): 795-803. DOI： 10.7638/kqdlxxb-2017.0144.

MA Chengyu, HE Guoyi, WANG Qi. Aerodynamic performance study on backswept blade of HALE UAV propeller[J]. 2019, 37(5): 795-803. DOI： 10.7638/kqdlxxb-2017.0144.

摘要

由于螺旋桨高速性能欠佳，飞行速度在偏离设计点时气动效率下降很快，以螺旋桨为推进系统的高空长航时无人机难以满足快速爬升和快速机动的设计要求。针对这一问题，将桨叶后掠设计方法应用于高空长航时无人机螺旋桨上，在无后掠桨叶的基础上，分别设计了后掠角为10°、20°、30°、40°、50°五个后掠桨叶。基于周期性边界条件和多重参考系方法求解三维N-S方程，对不同后掠桨叶的气动性能进行了计算。根据计算结果，分析了无后掠螺旋桨气动性能下降的原因和后掠对桨叶气动性能的影响。研究结果表明：高空长航时无人机螺旋桨气动性能下降的原因是定桨距螺旋桨桨叶迎角随飞行速度提高而减小以及桨尖压缩效应的影响；后掠桨叶能提供更大的拉力但也需要更大的功率，当后掠角度处在30°和50°之间时，螺旋桨高速性能最好；后掠桨叶螺旋桨的气动性能受迎角变化、桨尖三维效应、桨尖激波强度、激波-附面层干扰综合影响。

Abstract

In the high speed situation

the efficiency of propeller drops rapidly after design point with the performance of the propeller deteriorated sharply

and the high altitude long endurance (HALE) unmanned aerial vehicles (UAVs) are difficult to meet the design requirements for fast climbing and rapid maneuvering. The swept blade design method was used to solve this problem. Five swept blades were designed on the basis of unswept blade

and the sweep angles were 10°

20°

30°

40°

and 50°. Three dimensional Reynolds averaged Navier-Stokes(RANS) equations were solved based on periodic boundary condition

and multiple reference frames(MRF) model was employed to simulate the aerodynamic properties of unswept and swept blades. According to the results

the reason why the efficiency of propeller drops rapidly after design point was discussed firstly

and then the thrust

power and efficiency of different blades were compared. Moreover

the influence of swept design of blades was discussed through comparing the pressure distribution on each blade. The results show that the decreasing attack angle of blade with the increasing of flight speed as well as the tip compression effect of blade lead to the rapidly dropping efficiency of propeller after design point. The decreasing attack angle of blade can be avoided by changing the propeller rotational speed according to the changing of flight speed

however

the tip compression effect of blade always effected the propeller performance negatively no matter what the advance ratio is. The comparison of the thrust

power and efficiency between different sweep angles show that

the swept blade can provide higher thrust but need more power

and the high-speed performance of propeller is satisfactory when the sweep angle is between 30° and 50°. The comparison of the pressure distribution between different sweep angles shows that the performance of swept blades is influenced by the changed attack angle and the three-dimensional tip effect of the blade. The comparison of the tip pressure distribution between swept and unswept blades shows that the strength of the tip shock wave can be reduced by the swept blade method

but the interference of the shock wave/boundary layer contributes to the strength. In conclusion

the swept blade design method can reduce the impact of the tip compression effect on propeller

but the swept blade performance is influenced by the changed blade attack angle

the three-dimensional blade tip effect

the strength of the tip shock wave

and the shock wave/boundary layer interation.

关键词

Keywords

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