涡桨飞机滑流影响的非定常数值模拟验证

马率; 王建涛; 邱名; 刘刚

doi:10.7638/kqdlxxb-2017.0146

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涡桨飞机滑流影响的非定常数值模拟验证

研究论文 | 更新时间：2026-05-28

- 涡桨飞机滑流影响的非定常数值模拟验证
- Unsteady numerical simulation verification of slipstream effect on turboprop
- 空气动力学学报 2019年37卷第5期页码：804-812
- 作者机构：
  
  中国空气动力研究与发展中心计算空气动力研究所,绵阳,621000
- 作者简介：
  
  马率(1981-), 男, 四川绵阳人, 副研究员, 主要从事计算流体力学应用研究.E-mail:tuboshu2002@163.com
  刘刚(1964-), 男, 研究员, 研究方向:流动控制的CFD模拟
- 基金信息：
- DOI：10.7638/kqdlxxb-2017.0146
  中图分类号： V211.3
- 纸质出版：2019
- 稿件说明：
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马率, 王建涛, 邱名, 刘刚. 涡桨飞机滑流影响的非定常数值模拟验证[J]. 空气动力学学报, 2019, 37(5): 804-812.

MA Shuai, WANG Jiantao, QIU Ming, et al. Unsteady numerical simulation verification of slipstream effect on turboprop[J]. 2019, 37(5): 804-812.
马率, 王建涛, 邱名, 刘刚. 涡桨飞机滑流影响的非定常数值模拟验证[J]. 空气动力学学报, 2019, 37(5): 804-812. DOI： 10.7638/kqdlxxb-2017.0146.

MA Shuai, WANG Jiantao, QIU Ming, et al. Unsteady numerical simulation verification of slipstream effect on turboprop[J]. 2019, 37(5): 804-812. DOI： 10.7638/kqdlxxb-2017.0146.

摘要

通过求解绝对坐标系下的非定常雷诺平均Navier-Stokes方程，计算了螺旋桨非定常滑流对某涡桨飞机起飞构型低速状态的气动特性影响。为描述螺旋桨桨叶的相对运动，采用了动态重叠网格技术，并在并行环境下采用全隐式双时间步方法和多重网格技术来保证时间精度和提高计算效率，计算结果与试验值相当吻合，研究表明：滑流区内襟翼上的动压得到明显增强，同时高速滑流也起到一个吹除在大偏度襟翼上堆积的附面层作用，延迟了襟翼上气流的分离，这两个因素明显提高了襟翼效率，另外经过机翼的导流作用后，滑流对襟翼的洗流不像机翼那么明显。本文还将有无滑流的流场进行对比，通过当地动压增量来定义滑流的加速效应边界，以及通过当地气流角增量来定义滑流的洗流效应边界。该方法能较好地捕捉和解释滑流对飞机部件干扰而使得飞机方向安定性呈现的非线性现象，初步揭示了螺旋桨滑流复杂尾迹流动的特点。

Abstract

Unsteady compressible Reynolds-averaged Navier-Stokes equations in absolute coordinate system are solved to simulate the flow field which is affected by propeller slipstream in turbopro airplane takeoff states. A moving overlap grids technology is used to depict the relative motion of propeller blades. In order to guarantee the time precision and enhance computing efficiency

a fully implicit dual-time stepping method and multigrid scheme are used in parallel environment. The aerodynamic performance of airplane with propeller slipstream from numerical calculation agrees well with the experimental data. The results show that

the dynamic pressure of the flaps in the slipstream region is obviously increased

at the same time

because the slipstream blows away the accumulated boundary layer on the flaps

the slipstream delays the separation of the airflow on the flaps. These two factors mentioned above significantly improve the efficiency of the flaps

in addition

through the guide function of the flaps

the wash of the slipstream flow on the flaps is not as obvious as that on the wings. The acceleration effect boundary of the slipstream is acquired by local dynamic pressure increments and the wash effect boundary of the slipstream is gotten by local airflow angle increments. With this method

the non-linear phenomenon of the stability of the propeller aircraft

due to the interference effect of slipstream on air-craft components

can be well captured and explained. Also

the slipstream's wake convection and evolution can be revealed by the method. The present work provides certain reference for both propeller aircraft design and slipstream effect research.

关键词

Keywords

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