前缘带光滑霜冰的NACA0012翼型表面声学特性计算

肖春华; 姜裕标; 李明

doi:10.7638/kqdlxxb-2018.0094

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前缘带光滑霜冰的NACA0012翼型表面声学特性计算

研究论文 | 更新时间：2026-05-28

- 前缘带光滑霜冰的NACA0012翼型表面声学特性计算
- Computation of surface acoustic characteristics of NACA0012 airfoil with smooth rime ice on the leading edge
- 空气动力学学报 2019年37卷第6期页码：1010-1017
- 作者机构：
  
  1. 中国空气动力研究与发展中心空气动力学国家重点实验室,四川,绵阳,621000
  2. 中国空气动力研究与发展中心飞行器结冰与防除冰重点实验室,四川,绵阳,621000
- 作者简介：
  
  肖春华(1976-), 江西南康人, 男, 博士, 研究员, 主要研究方向:结冰机理与防除冰应用.E-mail:dragoner76@163.com
- 基金信息：
  
  国家自然科学基金面上项目（11572338）;国家重点基础研究计划（2015CB755804）
- DOI：10.7638/kqdlxxb-2018.0094
  中图分类号： V211.3
- 纸质出版：2019
- 稿件说明：
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肖春华, 姜裕标, 李明. 前缘带光滑霜冰的NACA0012翼型表面声学特性计算[J]. 空气动力学学报, 2019, 37(6): 1010-1017.

XIAO Chunhua, JIANG Yubiao, LI Ming. Computation of surface acoustic characteristics of NACA0012 airfoil with smooth rime ice on the leading edge[J]. 2019, 37(6): 1010-1017.
肖春华, 姜裕标, 李明. 前缘带光滑霜冰的NACA0012翼型表面声学特性计算[J]. 空气动力学学报, 2019, 37(6): 1010-1017. DOI： 10.7638/kqdlxxb-2018.0094.

XIAO Chunhua, JIANG Yubiao, LI Ming. Computation of surface acoustic characteristics of NACA0012 airfoil with smooth rime ice on the leading edge[J]. 2019, 37(6): 1010-1017. DOI： 10.7638/kqdlxxb-2018.0094.

摘要

结冰将改变飞机空气动力表面形状，不仅使飞机空气动力性能下降，还会导致气动噪声的变化。为研究结冰对翼型气动噪声的影响，采用计算流体力学方法对前缘带光滑霜冰的NACA0012翼型表面声学特性进行了数值计算。采用C型网格拓扑结构对结冰翼型的计算区域进行了划分，采用不可压缩雷诺平均N-S方程对结冰翼型周围黏性流场进行了数值计算，采用基于Proudman理论的宽频噪声模型和Curle的表面积分方法预测了结冰翼型的表面声学参数，获得了沿结冰翼型弦向分布的表面声功率和表面声功率级。研究表明，0°或小攻角时，靠近前缘霜冰区域的流动转捩或流动分离使结冰翼型的表面声功率更高；较大攻角时，靠近后缘的区域发生流动分离，使后缘的表面声功率增加，进一步增加了结冰翼型的表面声功率。前缘霜冰产生的流动转捩和流动分离是结冰翼型气动噪声增加的主要原因。

Abstract

Ice accretion can change the shape of airplane aerodynamic surface. Not only it can result in the degradation of aerodynamic performance

but also it can lead to the variation of aeroacoustic characteristics. In order to explore the effect of ice accretion on the aerodynamic noise

the surface acoustic characteristics of NACA0012 airfoil with smooth rime ice on the leading edge is studied numerically by the computational fluid dynamics method (CFD). C-type topology grids are generated to distribute the computational domain of iced airfoil. The incompressible Reynolds-averaged Navier-Stokes equations are used to simulate the viscous flow field around the iced airfoil. The broadband noise model based on Proudman theory and the Curle surface integral method are adopted to predict the surface acoustic parameters of the iced airfoil. The surface acoustic power and surface acoustic power level distribution along iced airfoil chordwise are obtained emphatically. It is shown that the flow transition or flow separation near the rime ice model on the leading edge results in high surface acoustic power of iced airfoil at zero or small angle of attack. Flow separation or flow transition appears in the region near the trailing edge

which can increase the surface acoustic power along the trailing edge at high angle of attack

further increasing surface acoustic power of the iced airfoil. The flow transition and flow separation on iced airfoil caused by the rime ice on the leading edge are the main reason for increasing aerodynamic noise.

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references

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