超声速喷流激波噪声基础问题数值模拟研究进展  

A brief review on the numerical studies of the fundamental problems for the shock associated noise of the supersonic jets

作　　者：张树海[1] 武从海 罗勇 韩帅斌 张俊龙[2] ZHANG Shuhai;WU Conghai;LUO Yong;HAN Shuaibin;ZHANG Junlong(State Key Laboratory of Aerodynamics,China Aerodynamics Research and Development Center,Mianyang 621000,China;Key Laboratory of Aerodynamics Noise Control,China Aerodynamic Research and Development Center,Mianyang 621000,China)

机构地区：[1]中国空气动力研究与发展中心空天飞行空气动力科学与技术全国重点实验室,绵阳621000 [2]中国空气动力研究与发展中心气动噪声控制重点实验室,绵阳621000

出　　处：《实验流体力学》2024年第1期1-27,共27页Journal of Experiments in Fluid Mechanics

摘　　要：超声速喷流问题是一个包含激波、旋涡、湍流和声波的多尺度复杂流动问题,其数值模拟方法及激波噪声产生机制是相关研究的长期热点和难点。本文简要回顾了超声速喷流激波噪声研究进展,重点介绍了针对激波噪声计算方法的非物理噪声消除技术和光滑因子设计准则,针对超声速喷流激波噪声研究设计的模型问题(包括旋涡–旋涡相互作用、激波–旋涡相互作用和激波–剪切层相互作用等),以及轴对称和三维超声速喷流的研究进展。本文还介绍了作者最近针对超声速喷流开展的三维直接数值模拟、实验验证工作和初步分析结果(包括轴对称模态定位、束缚波演化和摆动模态发展等)。The flow of the supersonic jets contains shock waves,vortices,turbulence and acoustic waves.The numerical simulation method and the mechanism of the shock associated noise of the supersonic jets have been topics of general interest.This paper contains two parts.Firstly,we briefly review the numerical studies on the fundamental problems of the shock associated noise of the supersonic jets.It includes the numerical methods for the shock associated noise,and the models of the supersonic jets,the axisymmetric and three dimensional supersonic jets.For the numerical method,we introduce the technique to reduce the non-physical oscillation and a criterion to design the smoothness indicator for high order shock capturing schemes.Secondly,we introduce our recent results based on the direct numerical simulations and experi-mental verification,including the localization of the axisymmetric modes,the development of trapped waves and the evolution of the flapping modes.

关 键 词：超声速喷流 激波 旋涡 湍流 噪声 数值模拟 

分 类 号：O354.5[理学—流体力学] V211.3[理学—力学]