超声速混合层气动声场的数值模拟

马利宇; 方一红

doi:10.7638/kqdlxxb-2017.0123

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超声速混合层气动声场的数值模拟

研究论文 | 更新时间：2026-05-28

- 超声速混合层气动声场的数值模拟
- Numerical simulation of acoustic radiation in supersonic mixing layer
- 空气动力学学报 2019年37卷第5期页码：770-776
- 作者机构：
  
  天津大学机械工程学院高速空气动力学研究室,天津,300072
- 作者简介：
  
  马利宇(1994-), 男, 山西人, 硕士研究生, 主要从事气动声学研究.E-mail:maliyu@tju.edu.cn
  方一红(1965-), 女, 上海人, 副教授, 主要从事流动稳定性及气动声学等研究.E-mail:yhfang@tju.edu.cn
- 基金信息：
  
  国家自然科学基金（91852110，11332007）
- DOI：10.7638/kqdlxxb-2017.0123
  中图分类号： V211.3
- 纸质出版：2019
- 稿件说明：
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马利宇, 方一红. 超声速混合层气动声场的数值模拟[J]. 空气动力学学报, 2019, 37(5): 770-776.

MA Liyu, FANG Yihong. Numerical simulation of acoustic radiation in supersonic mixing layer[J]. 2019, 37(5): 770-776.
马利宇, 方一红. 超声速混合层气动声场的数值模拟[J]. 空气动力学学报, 2019, 37(5): 770-776. DOI： 10.7638/kqdlxxb-2017.0123.

MA Liyu, FANG Yihong. Numerical simulation of acoustic radiation in supersonic mixing layer[J]. 2019, 37(5): 770-776. DOI： 10.7638/kqdlxxb-2017.0123.

摘要

超声速混合层的噪声是气动声学研究的经典问题，制约着航空发动机性能的提升。本文用数值方法对超声速混合层声辐射特性进行研究，具体方法：用抛物化稳定性方程（PSE）计算混合层近场大尺度扰动演化，结合一种基于渐进展开和稳定性分析的积分预测远场声压，得到快慢两种模态马赫波辐射的强度和方向。分析了上下侧来流温度对气动声场的影响，结果表明，上下侧温度比小于1时，慢模态占优；而上下侧温度比大于1时，快模态占优。

Abstract

The problem of acoustic radiation restricts the performance of aero-engine. To further reveal the acoustic radiation mechanism of mixing layer under supersonic flow

and enhance the understanding

this paper studies the acoustic characteristics of supersonic mixing layer. The near field calculation is investigated by numerical simulation of parabolized stability equations (PSE)

and an integral theory based on stability theory is applied to predict the far field acoustic pressure. The intensity and direction of Mach wave are calculated and in good agreement with previous results. The influence of the flow temperature at the upper and the lower sides is discussed in detail. The results show that

the slow mode dominates when the temperature ratio is less than 1

while the fast mode dominates when the temperature ratio is greater than 1.

关键词

Keywords

references

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