Aerodynamic performance study on backswept blade of HALE UAV propeller

MA Chengyu; HE Guoyi; WANG Qi

doi:10.7638/kqdlxxb-2017.0144

English Version Journal Login

您当前的位置：

首页 >

文章列表页 >

Aerodynamic performance study on backswept blade of HALE UAV propeller

更新时间：2026-05-28

- Aerodynamic performance study on backswept blade of HALE UAV propeller
- Vol. 37, Issue 5, Pages: 795-803(2019)
- 作者机构：
  
  南昌航空大学飞行器工程学院,南昌,330063
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2017.0144
  CLC： V211.44
- Published：2019
- 稿件说明：
移动端阅览
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

references

LIU P Q. Air propeller theory and its application[M]. Beijing:Beihang University Press, 2006. (in Chinese)

YANG X C, WANG Y T, MENG D H, et al. Study on wing slipstream effects of distributed propellers with different rotating directions[J]. Acta Aerodynamica Sinica, 2019(1):89-98. (in Chinese)

ALEKSANDROV. Air propeller[M]. Beijing:Higher Education Press, 1954. (in Chinese)

HAGER R D, VRABEL D. Advanced turboprop project. NASA SP-495[M]. NASA Special Publication, 1988, 495.

KOSMATKA J B, FRIEDMANN P P. Vibration analysis of composite turbopropellers using a nonlinear beam-type finite-element approach[J]. AIAA Journal, 1989, 27(11):1606-1614.

FARASSAT F, PADULA S L, DUNN M H. Advanced turboprop noise prediction based on recent theoretical results[J]. Journal of Sound and Vibration, 1987, 119(1):53-79.

ZHANG S, YU X Q. Model of open rotor engine for aircraft conceptual design[J]. Journal of Aerospace Power, 2012, 27(8):1801-1808. (in Chinese)

YAN C Z. Green power:open rotor aero-engine[J]. Aeronautical Science and Technology, 2013(1):6-12. (in Chinese)

TUZCU I, MARZOCCA P, CESTINO E, et al. Stability and control of a high-altitude, long-endurance UAV[J]. Journal of Guidance Control Dynamics, 2007, 30(3):713-721.

COLOZZA A. High altitude propeller design and analysis overview[J]. Federal Data Systems Cleveland Ohio, 1998, 44135.

KOCH L D. Design and performance calculations of a propeller for very high altitude flight[R]. NASA 1998-0017535, 1998.

WANG D Y, LI Y L. Key technology of unmanned aerial reconnaissance aircraft in high altitude long endurance[J]. Winged Missiles Journal, 2009(11):31-35. (in Chinese)

DENG H Q, YU X Q. Solar aircraft:status and directions[J]. Aeronautical Science and Technology, 2006(1);28-30. (in Chinese)

CHANG M, ZHOU Z, ZHENG Z C. Flight principles of solar-powered airplane and sensitivity analysis of its conceptual parameters[J]. Journal of Northwestern Ploytechnical University, 2010, 28(5):792-796. (in Chinese)

SWIDERLYONS K, SCHUETTE M, STROMAN R, et al. Liquid hydrogen fuel System for small unmanned air vehicles[C]//AIAA Aerospace Sciences Meeting. 2013: 963-972.

GONZÁLEZ-ESPASANDÍN ÓSCAR, LEO T J, NAVARRO-ARÉVALO EMILIO. Fuel cells:a real option for unmanned aerial vehicles propulsion[J]. The Scientific World Journal, 2014, 2014:1-12.

RODGERS J A. Hydrogen fuel cells for small unmanned air vehicles[J]. Ecs Transactions, 2017, 64(3):963-972.

ZHU B, CHEN X N, FAN T Y. Development analysis of high altitude long endurance UAVs abroad[J]. Pace System and Technology, 2013(11):28-32. (in Chinese)

LI Y P. Conceptual design for solar/hydrogen hybrid powered small-scale UAV[D]. Beijing Institute of Technology, 2014. (in Chinese)

LIU L, DU M Y, ZHANG X H, et al. Conceptual design and energy management strategy for UAV with hybrid solar and hydrogen energy[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(1):144-162. (in Chinese)

TAO Y J. Development and key technology on near space long voyage solar unmanned aerial vehicle[J]. Aeronautical Manufacturing Technology, 2016, 513(18):26-30. (in Chinese)

LIU P Q, MA L C, QU Q L, et al. Numerical investigation of the laminar separation bubble control by blowing/suction on an airfoil at low Re number[J]. Acta Aerodynamica Sinica, 2013, 31(4):518-524. (in Chinese)

LI G Q, ZHOU S Y, NI Z S, et al. Research on performance enhancement of stratophere propeller using plasma in muti-operating mode[J]. Aeronautical Computing Technique, 2014(2):26-31. (in Chinese).

ZHU M, YANG X D, SONG C, et al. High synergy method for near space propeller using co-flow jet control[J]. Acta Aeronautica et Astronautica Sinica, 2014, 35(6):1549-1559. (in Chinese)

ZHANG W L, TANG J J, CHEN Z H, et al. Optimization of suction control on separation flow around an airfoil at low Reynolds number[J]. Acta Aerodynamica Sinica, 2015, 33(6):757-764. (in Chinese).

WANG K L, ZHU X P, ZHOU Z, et al. Distributed electric propulsion slipstream aerodynamic effects at low Reynolds number[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(9):2669-2678. (in Chinese)

WANG K L, ZHOU Z, ZHU X P. Aerodynamic design of low-Reynolds number wing taking into account the multiple propellers induced effects[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(6):120813. (in Chinese)

NIE Y. The design and experiments study on high efficient propeller used for stratospheric airship[D]. University of Chinese Academy of Sciences, 2008. (in Chinese)

MORGADO J, ABDOLLAHZADEH M, SILVESTRE M A R, et al. High altitude propeller design and analysis[J]. Aerospace Science and Technology, 2015, 45:398-407.

CHEN G Q, BAI P, ZHAN H L, et al. Numerical simulation study on propeller slipstream effect on unmanned air vehicle with propeller engine[J]. Acta Aerodynamica Sinica, 2015, 33(4):554-562. (in Chinese)

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Parametric construction of blade leading and trailing edges with arbitrary central angles using NURBS curves

Influence of windbreak distance on the aerodynamic performance of high-speed trains by large eddy simulation

Research progress on propeller aerodynamic design of low-altitude electric vertical take-off and landing aircraft

Research progress on Reynolds number effects in the design of large aircraft

Flow characteristic analysis and optimization design of a bionic dragonfly vertical takeoff and landing nozzle

Related Author

CHEN Jianjun

XIA Yifan

XU Jingchao

NI Haonan

YANG Yonggang

LI Rui

JIA Yongxing

ZHAO Gaopeng

Related Institution

School of Aeronautics and Astronautics, Zhejiang University, Hangzhou

School of Mechanical and Electrical Engineering, Lanzhou Jiaotong University, Lanzhou

National Key Laboratory of Aircraft Configuration Design, Xi’an

School of Aeronautics, Northwestern Polytechnical University, Xi’an

National Key Laboratory of Aircraft Configuration Design, Xi'an

AI问答

⁰