基于气动载荷分布的螺旋桨诱导流场重构设计

王科雷; 周洲; 祝小平; 郭佳豪; 范中允

doi:10.7527/S1000-6893.2019.23118

航空学报 >

2020 , Vol. 41 >Issue 1: 123118 - 123118

DOI: https://doi.org/10.7527/S1000-6893.2019.23118

流体力学与飞行力学

基于气动载荷分布的螺旋桨诱导流场重构设计

王科雷 ,
周洲 ,
祝小平 ,
郭佳豪 ,
范中允

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1. 西北工业大学航空学院, 西安 710072;
2. 西北工业大学长三角研究院, 太仓 215400;
3. 西北工业大学航天学院, 西安 710072

收稿日期: 2019-04-29

修回日期: 2019-07-11

网络出版日期: 2019-07-22

基金资助

装备预研项目（41411020401）；民机专项（MJ-2015-F-009）；大院大所创新引领专项计划（TC2018DYDS24）

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Reconstruction design of propeller induced flow-field based on aerodynamic loading distributions

WANG Kelei ,
ZHOU Zhou ,
ZHU Xiaoping ,
GUO Jiahao ,
FAN Zhongyun

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1. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China;
2. Yangtze River Delta Research Institute, Northwestern Polytechnical University, Taicang 215400, China;
3. School of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China

Received date: 2019-04-29

Revised date: 2019-07-11

Online published: 2019-07-22

Supported by

Equipment Pre-research Program (41411020401); Civil Aircraft Project (MJ-2015-F-009); Taicang Innovation Leading Institute Project (TC2018DYDS24)

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摘要

基于分布式电推进飞行器创新性发展理念，以螺旋桨滑流耦合下机翼气动效率最优为目标开展螺旋桨诱导流场重构设计研究。首先，通过构建基于动量源方法的准定常数值模拟技术，建立了螺旋桨桨盘载荷分布与诱导流场特性之间的联系；然后，基于对螺旋桨桨盘气动载荷分布曲线的参数化控制，提出了螺旋桨诱导流场重构优化设计思想及设计方法；最后，通过相关设计结果的对比分析验证了所提出螺旋桨诱导流场重构设计思想及设计方法的有效性和可靠性。结果表明：与等拉力最小诱导损失螺旋桨相比较，基于所提出诱导流场重构设计思想设计得到的螺旋桨最优气动载荷分布耦合下的机翼气动效率得到显著改善，在本文设计状态下，机翼翼段计算升力相对提高10.40%，计算阻力相对降低7.05%，计算升阻比相对增大18.77%。

关键词： 分布式电推进; 螺旋桨; 动量源; 气动载荷分布; 流场重构

本文引用格式

王科雷 , 周洲 , 祝小平 , 郭佳豪 , 范中允 . 基于气动载荷分布的螺旋桨诱导流场重构设计[J]. 航空学报, 2020 , 41(1) : 123118 -123118 . DOI: 10.7527/S1000-6893.2019.23118

Abstract

Based on the innovative developing concept of the distributed electric propulsion aircrafts, the reconstruction design of the propeller induced flow-filed is carried out in this study to obtain the maximum propeller/wing integrated aerodynamic efficiency. First, the quasi-steady numerical simulation technique is developed based on the momentum source method, then the relationship between the aerodynamic loading distributions and the propeller induced flow-field properties is established. Second, the optimization design method developed for the reconstruction of the propeller induced flow-field is proposed by controlling the parameterized aerodynamic loading distribution profiles. Finally, both the reliability and efficiency of the proposed aerodynamic design concept are studied. The results show that compared with the minimum induced loss propeller, the optimized aerodynamic loading distributions on the propeller disk lead to significant improvement of the wing aerodynamic performance under the slipstream effect. As a result, the wing section has a relative lift augmentation of 10.40%, a relative drag decrease of 7.05%, and a relative lift-to-drag increment of 18.77%.

Key words： distributed electric propulsion; propeller; momentum source; aerodynamic loading distribution; flow-field reconstruction

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