Numerical investigation of propeller slipstream effects on high-lift aerodynamic configurations

YANG Longyuan; SHENG Yunyi; CUI Tianyu; YANG Yong

doi:10.7638/kqdlxxb-2024.0090

English Version Journal Login

您当前的位置：

首页 >

文章列表页 >

Numerical investigation of propeller slipstream effects on high-lift aerodynamic configurations

更新时间：2026-05-28

- Numerical investigation of propeller slipstream effects on high-lift aerodynamic configurations
- Vol. 43, Issue 5, Pages: 41-50(2025)
- 作者机构：
  
  西北工业大学飞行器基础布局全国重点实验室,西安,710072
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2024.0090
  CLC： V211.3
- Published：2025
- 稿件说明：
移动端阅览
杨龙源, 盛云逸, 崔天昱, 等. 螺旋桨滑流对高升力构型影响的数值计算[J]. 空气动力学学报, 2025, 43(5): 41−50.

YANG Longyuan, SHENG Yunyi, CUI Tianyu, et al. Numerical investigation of propeller slipstream effects on high-lift aerodynamic configurations[J]. 2025, 43(5): 41-50.
杨龙源, 盛云逸, 崔天昱, 等. 螺旋桨滑流对高升力构型影响的数值计算[J]. 空气动力学学报, 2025, 43(5): 41−50. DOI： 10.7638/kqdlxxb-2024.0090

YANG Longyuan, SHENG Yunyi, CUI Tianyu, et al. Numerical investigation of propeller slipstream effects on high-lift aerodynamic configurations[J]. 2025, 43(5): 41-50. DOI： 10.7638/kqdlxxb-2024.0090.

摘要

为了快速、准确分析螺旋桨滑流对增升装置的影响，采用实桨非定常方法（full blades method

FBM）和定常动量激励盘方法（actuator disk method

ADM），数值计算分析了前进比

= 0.7、1.0，攻角

= –4°～24°工况下螺旋桨滑流对高升力构型的影响。研究表明：虽然从单独螺旋桨获取的时均化激励盘载荷分布与从高升力构型螺旋桨获取的存在局部差异，但将来源不同的激励盘载荷应用于ADM计算时，所得高升力构型的压力分布、升阻力结果基本一致，全机升力系数差异不超过4.3%，阻力系数偏差小于5.4%，说明采用单独螺旋桨获取激励盘载荷对全机气动力计算影响不大，从而避免了复杂的网格生成。ADM将非定常计算转化为定常计算，在保持网格量相当（

3300

万）的条件下，其计算结果与FBM结果在失速前（

＜20°时）基本吻合，同时计算核时约降低至FBM的1/18（170/

3100

）。因此 ADM方法能够高效、合理评估出螺旋桨滑流对增升装置产生的影响。

Abstract

To achieve rapid and accurate analysis of propeller slipstream effects on high-lift configurations

this study employed both the full blades method (FBM) and actuator disk method (ADM) for numerical simulations under advance ratios

= 0.7

1.0 and angles of attack ranging from –4° to 24°. The results showed that although there were local differences in time-averaged actuator disk load distrib

utions between isolated propellers and propellers integrated with high-lift configurations

the pressure distributions and lift/drag results obtained by applying these different load sources in ADM calculations were fundamentally consistent. The differences in overall lift coefficient did not exceed 4.3%

and drag coefficient deviations remain below 5.4%

demonstrating that using actuator disk loads from isolated propellers had minimal impact on full-aircraft aerodynamic calculations

thereby avoiding complex grid generation. By converting unsteady computations to steady-state solutions while maintaining equivalent grid resolution (33 million cells)

ADM achieved results that closely match FBM before stall (

＜ 20°)

with computational time reduced to approximately 1/18 of FBM (170 vs.

3100

core-hours). The ADM method thus provides an efficient and reasonable approach for evaluating propeller slipstream effects on high-lift devices.

关键词

Keywords

references

O'BRIEN D M. Analysis of computational modeling techniques for complete rotorcraft configurations (Order No. 3212277) [D].Georgia Institute of Technology, 2006. https://www.proquest.com

IKAMI T, FUJITA K, NAGAI H. Unsteady flow field on wing surface in propeller slipstream at low Reynolds number[C]// AIAA Aviation 2022 Forum, Chicago, IL Virtual. AIAA, 2022: AIAA 2022-3983. doi: 10.2514/6.2022-3983

XUE C, ZHOU Z. Propeller-wing coupled aerodynamic design based on desired propeller slipstream[J]. Aerospace Science and Technology, 2020, 97: 105556. doi: 10.1016/j.ast.2019.105556

BOUSQUET J M, GARDAREIN P. Improvements on computations of high speed propeller unsteady aerodynamics[J]. Aerospace Science and Technology, 2003, 7(6): 465−472. doi: 10.1016/S1270-9638(03)00046-4

ROOSENBOOM E W M, STÜRMER A, SCHRÖDER A. Advanced experimental and numerical validation and analysis of propeller slipstream flows[J]. Journal of Aircraft, 2010, 47(1): 284−291. doi: 10.2514/1.45961

GONG X L, YANG Y, XIA Z F. Unsteady simulation method and actuator disk theory in numerical simulations of propeller's interference on wing[J]. Aeronautical Computing Technique, 2012, 42(1): 76−79 (in Chinese). doi: 10.3969/j.issn.1671-654X.2012.01.021

XIA Z F, LUO S, YANG Y. Numerical simulations of propeller slipstream flows using actuator disk theory[J]. Acta Aerodynamica Sinica, 2012, 30(2): 219−222,232 (in Chinese). doi: 10.3969/j.issn.0258-1825.2012.02.015

RAICHLE A, MELBER-WILKENDING S, HIMISCH J. A new actuator disk model for the TAU code and application to a sailplaine with a folding engine[M]//New Results in Numerical and Experimental Fluid Mechanics Ⅵ. Berlin, Heidelberg: Springer Berlin Heidelberg, 2007: 52−61. doi: 10.1007/978-3-540-74460-3_7

VELDHUIS L L M. Review of propeller-wing aerodynamic interference [C]//24th International Congress of the Aeronautical Sciences, Yokohama, Japan. Beijing: Chinese Society of Aeronautics and Astronautics, 2004.

SAMANT S S, YU N J. Flow prediction for propfan engine installation effects on transport aircraft at transonic speeds: NASA CR-3954 [R]. California, USA: National aeronautics and space administration, 1986.

MOENS F, GARDAREIN P. Numerical simulation of the propeller/wing interaction for transport aircraft: AIAA-2001-2404 [R]. Anaheim, CA, USA: American Institute of Aeronautics and Astronautics, 2001.

ZACHARIADIS A, HALL C A. Application of a navier–stokes solver to the study of open rotor aerodynamics[J]. Journal of Turbomachinery, 2011, 133(3): 031025. doi: 10.1115/1.4001246

CUSATI V, CORCIONE S, NICOLOSI F, et al. Improvement of take-off performance for an electric commuter aircraft due to distributed electric propulsion[J]. Aerospace, 2023, 10(3): 276. doi: 10.3390/aerospace10030276

LI B, LIANG D W, HUANG G P. Propeller slipstream effects on aerodynamic performance of turbo-prop airplane based on equivalent actuator disk model[J]. Acta Aeronautica et Astronautica Sinica, 2008, 29(4): 845−852 (in Chinese). doi: 10.3321/j.issn:1000-6893.2008.04.013

LE CHUITON F. Actuator disc modelling for helicopter rotors[J]. Aerospace Science and Technology, 2004, 8(4): 285−297. doi: 10.1016/j.ast.2003.10.004

KHIER W. Time-accurate versus actuator disk simulations of complete helicopters[M]//High Performance Computing in Science and Engineering' 05. Berlin/Heidelberg: Springer-Verlag, 2006: 209−220. doi:10.1007/3-540-29064-8_16

STRASH D, LEDNICER D, RUBIN T. Analysis of propeller-induced aerodynamic effects[C]// 16th AIAA Applied Aerodynamics Conference, Albuquerque, NM, USA. AIAA, 1998: AIAA 1998-2414. doi:10.2514/6.1998-2414

AMATO M, BOYLE F, EATON J A, et al. Euler/Navier stokes simulation for propulsion-airframe integration of advanced propeller driven aircraft in the European research programs GEMINI/APIAN [C] // 21st Congress of International Council of the Aeronautical Sciences, Melbourne, Australia, 1998.

WALES C, JONES D, GAITONDE A, et al. Comparison of aircraft loads using URANS and actuator disk modelling of propellers[C]// AIAA Aviation 2022 Forum, Chicago, IL Virtual. AIAA, 2022: AIAA 2022-3684. doi: 10.2514/6.2022-3684

WALES C, JONES D, GAITONDE A. Comparison of aircraft loads using URANS and actuator disk modelling of propellers at high incidence[C]// AIAA AVIATION 2023 San Diego, CA and Online. AIAA, 2023: AIAA 2023-3670. doi: 10.2514/6.2023-3670

RONCH A D, VALLESPIN D, GHOREYSHI M. Evaluation of dynamic derivatives using computational fluid dynamics[J]. AIAA Journal, 2012, 50: 470−484. doi: 10.2514/1.J051304

ANDERSON J D. Computational fluid dynamics: The basic with applications [M]. New York: McGraw–Hill Higher Education, 1995: 49−74.

WANG W, YANG Y, XIA Z F. Study on comparison of different numerical simulation methods concerning propeller slipstream[J]. Aeronautical Computing Technique, 2012, 42(5): 80−83,86 (in Chinese). doi: 10.3969/j.issn.1671-654X.2012.05.020

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Impact of key area optimization on the aerodynamic characteristics of a high-speed train in crosswind

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

Numerical simulation of liquid film cooling on hypersonic oblique plate

Performance of various SST models in predicting typical separated flows

Aerodynamic characteristics of seagull bionic airfoil based on breathable structure

Related Author

Jiang Jiyun

Liu Tanghong

Wang Xinran

Gao Hongrui

Wang Lei

Jia Xiaofeng

Huang Wen

Hu Chuanxin

Related Institution

中南大学交通运输工程学院，轨道交通安全教育部重点实验室

中南大学轨道交通安全关键技术国际合作联合实验室

中南大学轨道交通列车安全保障技术国家地方联合工程研究中心

中车长春轨道客车股份有限公司

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

AI问答

⁰