几何外形变化对串联翼型干扰噪声的影响

张驰; 宋文滨

doi:10.7638/kqdlxxb-2018.0129

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几何外形变化对串联翼型干扰噪声的影响

研究论文 | 更新时间：2026-05-28

- 几何外形变化对串联翼型干扰噪声的影响
- Effects of geometry variations on tandem airfoil interaction noise
- 空气动力学学报 2020年38卷第3期页码：479-489
- 作者机构：
  
  上海交通大学航空航天学院,上海,200240
- 作者简介：
  
  张驰(1993-), 男, 湖北潜江人, 硕士研究生, 主要研究方向:气动噪声.E-mail:chizhang.zc@outlook.com
- 基金信息：
  
  工信部民机专项“先进高效增升装置气动设计技术”(2016-2019)
- DOI：10.7638/kqdlxxb-2018.0129
  中图分类号： V211.3;V224
- 纸质出版：2020
- 稿件说明：
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张驰, 宋文滨. 几何外形变化对串联翼型干扰噪声的影响[J]. 空气动力学学报, 2020, 38(3): 479-489.

ZHANG Chi, SONG Wenbin. Effects of geometry variations on tandem airfoil interaction noise[J]. 2020, 38(3): 479-489.
张驰, 宋文滨. 几何外形变化对串联翼型干扰噪声的影响[J]. 空气动力学学报, 2020, 38(3): 479-489. DOI： 10.7638/kqdlxxb-2018.0129.

ZHANG Chi, SONG Wenbin. Effects of geometry variations on tandem airfoil interaction noise[J]. 2020, 38(3): 479-489. DOI： 10.7638/kqdlxxb-2018.0129.

摘要

在应用的串联翼型构型中，前后翼型之间可能存在的流动干扰的效果之一是带来干扰噪声。针对串联机翼构型的气动干扰噪声问题，采用基于高阶数值格式的大涡模拟(LES)方法对流场进行了分析，然后通过FW-H方法得到了远场噪声结果。研究中首先针对基准构型进行了流场的计算结果分析和压力脉动的频谱分析，以及声学结果分析。在此基础上，通过改变前翼和后翼的几何外形参数，采用Kriging响应面方法，研究了两者变化的组合对干扰噪声的影响，其中重点在于前翼的尾缘外形和后翼的前缘外形参数变化的影响。通过分析响应面结果，给出了单个参数和多参数的影响规律。从声学结果来看，对于文中的翼型类型，最大厚度和后缘的船尾角应同步变化，并且不应过大或者过小。结果同时表明，通过调整几何外形，能够使得串联机翼的整体噪声更低。

Abstract

Interaction noise of a tandem airfoil configuration is studied using high-order large eddy simulations (LES) methods on a multi-block structured grid. The sound could be generated from aerodynamic interactions between the two airfoils positioned one after the other. The flow field is first calculated

and spectral properties of pressure fluctuations at a few given observation points are analyzed. The far-field noise obtained using FW-H integration is presented for the base configuration. The interaction from the wake of the airfoil in the front could interact with the leading edge of the trailing airfoil for specific configuration settings. The geometric features of both airfoils are also varied simultaneously to study the combined effects on the noise. The impact of geometric characteristics of trailing-edge and leading-edge of the front and rear airfoil

respectively

is the focus of the research. A typical surrogate-based approach is deployed in this study to reduce computational costs. The results show that

by careful tuning of the geometry and configuration

aeroacoustic characteristics of the tandem airfoil configuration could be modified to achieve lower acoustic levels.

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