考虑滑流影响的分布式螺旋桨布局优化设计

杨伟; 范召林; 吴文华; 余雷

doi:10.7638/kqdlxxb-2020.0189

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考虑滑流影响的分布式螺旋桨布局优化设计

研究论文 | 更新时间：2026-05-28

- 考虑滑流影响的分布式螺旋桨布局优化设计
- Optimal design of distributed propeller layout considering slipstream effect
- 空气动力学学报 2021年39卷第3期页码：71-79
- 作者机构：
  
  1. 国防科技大学空天科学学院,长沙,410073
  2. 中国空气动力研究与发展中心,绵阳,621000
- 作者简介：
  
  杨伟（1986-），男，四川梓潼人，助理研究员，研究方向：计算流体力学. E-mail：yangwei_cardc@sina.com
  吴文华*，江西宜黄人，研究员，研究方向：飞行器气动布局优化. E-mail：619677947@qq.com
- 基金信息：
  
  中国空气动力研究与发展中心基础与前沿技术研究基金（2019-046）
- DOI：10.7638/kqdlxxb-2020.0189
  中图分类号： V221.3
- 纸质出版：2021
- 稿件说明：
移动端阅览
杨伟, 范召林, 吴文华, 等. 考虑滑流影响的分布式螺旋桨布局优化设计[J]. 空气动力学学报, 2021, 39(3): 71−79.

YANG Wei, FAN Zhaolin, WU Wenhua, et al. Optimal design of distributed propeller layout considering slipstream effect[J]. 2021, 39(3): 71-79.
杨伟, 范召林, 吴文华, 等. 考虑滑流影响的分布式螺旋桨布局优化设计[J]. 空气动力学学报, 2021, 39(3): 71−79. DOI： 10.7638/kqdlxxb-2020.0189

YANG Wei, FAN Zhaolin, WU Wenhua, et al. Optimal design of distributed propeller layout considering slipstream effect[J]. 2021, 39(3): 71-79. DOI： 10.7638/kqdlxxb-2020.0189.

摘要

相对于传统螺旋桨飞机，前缘分布式螺旋桨飞机的滑流对整个机翼周围的流场特性影响更大。在分布式螺旋桨飞机动力布局设计过程中，应当考虑螺旋桨布局对滑流和机翼绕流的影响，使得机翼在滑流作用下表现出更好的气动特性。首先，基于雷诺平均Navier-Stokes方程，用等效盘代替真实螺旋桨，并采用重叠网格方法进行网格布局，优化过程中快速自动生成流场计算网格，获得机翼在滑流影响下的气动数据。然后，基于量子粒子群寻优算法建立分布式螺旋桨布局优化设计系统，使用该系统对采用NACA4412翼型的平直机翼和5个前缘分布式螺旋桨组成的构型进行了分布式螺旋桨布局优化设计。结果表明：等效盘模型能够对分布式螺旋桨滑流进行高效的数值模拟；优化后的分布式螺旋桨动力布局能使构型在起飞状态下升力系数提高5.6%，同时阻力系数减小13.9%。因此，建立的考虑滑流影响下机翼气动特性的分布式螺旋桨动力布局优化设计方法是可行且有工程应用价值的。

Abstract

Compared to conventional propeller planes

leading-edge distributed propeller aircrafts experience more severe impact of the slipstream effect. Such an effect ought to be taken into account in the design of the layout of distributed propellers

so that the aircrafts can achieve better aerodynamic characteristics. In the present study

the slipstream was simulated with an equivalent actuator disk model instead of real propellers based on the Navier-Stokes equations. The reliability and accuracy of the employed equivalent actuator disk model were verified. Overset method was used to combine both grids of the equivalent actuator disk and the wing to generate integrated computation

so that the computational grids and aerodynamic data for the wing under slipstream effects could be obtained automatically and rapidly during the optimization process. The optimization process for the distributed propeller layout design was established based on quantum particle swarm optimization algorithm

which was applied to distributed propeller layout design of a configuration employing a straight wing of NACA4412 airfoil and five leading-edge propellers. Results indicates that (a) the slipstream of distributed propellers can be simulated by the equivalent actuator disk efficiently and accurately; (b) lift and drag performance of the wing can be greatly improved with the optimization system taking into account the slipstream effect of the distributed propellers

and the configuration with the optimized propeller layout presents a lift increase of 5.6% and a drag reduction of 13.9% under the taking off condition. Therefore

the proposed optimization system is practical and valuable for distributed propeller layout design under slipstream effects.

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references

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