Aerodynamic characteristics and vortex ring features of propeller in vertical descent

GAO Zeming; SHAO Xueming; WANG Jiading; ZENG Lifang; LI Jun

doi:10.7638/kqdlxxb-2024.0009

English Version Journal Login

您当前的位置：

首页 >

文章列表页 >

Aerodynamic characteristics and vortex ring features of propeller in vertical descent

更新时间：2026-05-28

- Aerodynamic characteristics and vortex ring features of propeller in vertical descent
- Vol. 43, Issue 1, Pages: 1-11(2025)
- 作者机构：
  
  浙江大学航空航天学院,杭州,310027
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2024.0009
  CLC： V211.52
- Published：2025
- 稿件说明：
移动端阅览
高泽明, 邵雪明, 王家鼎, 等. 垂直下降状态下螺旋桨气动特性及涡环特征[J]. 空气动力学学报, 2025, 43(1): 1−11.

GAO Zeming, SHAO Xueming, WANG Jiading, et al. Aerodynamic characteristics and vortex ring features of propeller in vertical descent[J]. 2025, 43(1): 1-11.
高泽明, 邵雪明, 王家鼎, 等. 垂直下降状态下螺旋桨气动特性及涡环特征[J]. 空气动力学学报, 2025, 43(1): 1−11. DOI： 10.7638/kqdlxxb-2024.0009

GAO Zeming, SHAO Xueming, WANG Jiading, et al. Aerodynamic characteristics and vortex ring features of propeller in vertical descent[J]. 2025, 43(1): 1-11. DOI： 10.7638/kqdlxxb-2024.0009.

摘要

螺旋桨在垂直下降状态下极易进入涡环状态，从而引起复杂的空气动力学特性。采用黏性涡粒子方法（viscous vortex particle method

VVPM），对APC thin electric 10X7 螺旋桨在不同垂直下降率下的气动特性和涡环特征开展研究。结果表明：螺旋桨气动特性容易受到下降率的影响，当下降率增加时，拉力呈现先略增大再减小后增大的趋势，同时尾迹压缩效应逐渐增强，涡环中心逐渐上移。在此过程中，涡环先后经历了悬停状态、涡环前期、涡环初期、深度涡环和类风车流动状态，涡环特征从管状螺旋下洗涡逐渐演变成螺旋涡与环形涡并存，再到完全涡环结构，最后涡系结构移动至桨盘上方。涡场拓扑结构的演变直接影响螺旋桨的气动特性，当桨盘附近尾迹为管状螺旋涡结构时，螺旋桨气动特性变化不明显；随着下降率的增加，逐渐演变出的环形涡会严重影响螺旋桨的气动特性，表现为拉力骤降，尾迹压缩效应增强，回流区包裹桨盘；随着下降率进一步增加，涡系结构到达桨盘上方，螺旋桨进入类风车状态，气动力逐渐增大。

Abstract

Propellers are susceptible to entering the perilous vortex ring state during vertical descent

a phenomenon that results in complex aerodynamic characteristics that remain incompletely understood. utilizing the viscous vortex particle method (VVPM)

a thorough investigation was conducted on the aerodynamic characteristics and vortex ring features of the APC thin electric 10X7 propeller at different vertical descent rates. Results show that the propeller's aerodynamic characteristics are highly susceptible to changes in the descent rate. Specifically

as the vertical descent rate increases

the thrust initially experiences a slight increase

followed by a decrease

and ultimately a subsequent increase. Concurrently

the wake compression effect becomes progressively more pronounced

and the vortex ring center gradually shifts upwards. During this process

the vortex ring state transitions sequentially from hovering to a fully developed state

and ultimately transforms into a windmill-like flow state. The wake fields of the propeller gradually change from tubular helicoidal downwash vortical structures to a coexistence of tubular and toroidal vortical structures

and then to fully toroidal ones

which finally migrate completely to the top of the propeller disk. Such a topological evolution of the vortex field has a direct impact on the propeller's aerodynamic characteristics. Tubular helicoidal vortical structures exert negligible influence

while toroidal vortical structures have a significant impact as the descent rate increases

manifested in a sudden thrust decrease

the enhancement of the wake compression effect

the encirclement of propeller discs by backflows

and an increased aerodynamic force.

关键词

Keywords

references

LEISHMAN J G, BAGAI A . Challenges in understanding the vortex dynamics of helicopter rotor wakes[J ] . AIAA Journal, 1998 , 36 : 1130 − 1140 .

WANG S C. Aerodynamics of helicopter[M]. Beijing: Aviation Industry Press, 1985: 135(in Chinese).

LI G H. Study of high resolution numerical method for helicopter rotor in vortex ring state[D]. Shanghai: Shanghai Jiao Tong University, 2018: 20-25(in Chinese).

MEIJER DREES I J, HENDAL I W P . Airflow patterns in the neighbourhood of helicopter rotors: A description of some smoke tests carried out in a wind tunnel at Amsterdam[J ] . Aircraft Engineering and Aerospace Technology, 1951 , 23 ( 4 ): 107 − 111 .

WASHIZU K, AZUMA A, KOO J, et al. Experimental study on the unsteady aerodynamics of a model helicopter rotor operating in the vortex ring state[C]//Symposium on Structural Dynamics and Aeroelasticity. Boston, MA: AIAA, 1965.

GREEN R B, GILLIES E A, BROWN R E . The flow field around a rotor in axial descent[J ] . Journal of Fluid Mechanics, 2005 , 534 : 237 − 261 .

XIN H, GAO Z . Determination of boundary envelope of helicopter vortex ring area[J ] . Aerodynamic Experiment and Measurement Control, 1996 , 10 ( 1 ): 14 − 19 (in Chinese).

MA H R, MU Z T, LI H W, et al . Revised calculation method f or helicopter vortex-ring state boundary based on flight attitude[J ] . Acta Aerodynamica Sinica, 2018 , 36 ( 1 ): 31 − 34 (in Chinese).

LEISHMAN J G, BHAGWAT M J, ANANTHAN S . The vortex ring state as a spatially and temporally developing wake instability[J ] . Journal of the American Helicopter Society, 2004 , 49 ( 2 ): 160 − 175 .

LI P, CHEN R L . Rotor tip vortex model and its effect on free-vortex wake analysis[J ] . Acta Aeronautica et Astronautica Sinica, 2010 , 31 ( 8 ): 1517 − 1523 (in Chinese).

DZIUBINSKI A, STALEWSKI W. Vortex ring state simulation using actuator disc[C]//ECMS 2007 Proceedings, ECMS, 2007.

GRZEGORCZYK K . Analysis of the influence of helicopter descent velocity changes on the phenomenon of vortex ring state[J ] . Advances in Science and Technology – Research Journal, 2013 , 7 ( 17 ): 35 − 41 .

WANG J J, CHEN R L, WANG Z J, et al . Numerical simulation and mathematical modeling of vortex ring state of Tiltrotor aircraft[J ] . Journal of Harbin Institute of Technology, 2023 , 55 ( 4 ): 35 − 43 (in Chinese).

MIMEAU C, MORTAZAVI I . A review of vortex methods and their applications: From creation to recent advances[J ] . Fluids, 2021 , 6 ( 2 ): 68 .

WANG L Q, HE L, XU G H, et al . Investigation of helicopter rotor aeroacoustic characteristics in vortex ring state[J ] . Acta Aerodynamica Sinica, 2022 , 40 ( 6 ): 83 − 91 (in Chinese).

ZANOTTI A, ALGAROTTI D . Aerodynamic interaction between tandem overlapping propellers in eVTOL airplane mode flight condition[J ] . Aerospace Science and Technology, 2022 , 124 : 107518 .

HE C J, ZHAO J G . Modeling rotor wake dynamics with viscous vortex particle method[J ] . AIAA Journal, 2009 , 47 ( 4 ): 902 − 915 .

WEI P, SHI Y J, XU G H, et al . Numerical method for simulating rotor flow field based upon viscous vortex model[J ] . Acta Aeronautica et Astronautica Sinica, 2012 , 33 ( 5 ): 771 − 780 (in Chinese).

LEE H, LEE D J . Rotor interactional effects on aerodynamic and noise characteristics of a small multirotor unmanned aerial vehicle[J ] . Physics of Fluids, 2020 , 32 ( 4 ): 047107 .

CARADONNA F X, TUNG C. Experimental and analytical studies of a model helicopter rotor in hover: NASA-TM-81232[R]. 1980.

MCCRINK M H, GREGORY J W . Blade element momentum modeling of low-reynolds electric propulsion systems[J ] . Journal of Aircraft, 2017 , 54 ( 1 ): 163 − 176 .

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Static aerodynamic characteristics of symmetrical wind turbine airfoils considering the influence of near-ocean underlying surface

Aerodynamic characteristics of combined wing-tip link UAV

Aerodynamic characteristics of seagull bionic airfoil based on breathable structure

Multi-fidelity aerodynamic modeling method based on GPR model

Experimental investigation of vortex generator influence on wind turbine airfoil aerodynamic performance under turbulent inflow conditions

Related Author

Jia Xiaofeng

Huang Wen

Hu Chuanxin

Xu Xinye

Wang Han

Xu Xiaoping

Wang Guichen

Li Yunlong

Related Institution

School of urban construction, Wuhan University of Science and Technology, Wuhan

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

School of Aeronautics, Northwestern Polytechnical University, Xi'an

AI问答

⁰