亚声速二喉道流场不对称现象研究  

Research on asymmetric field flow in the subsonic second throat

作　　者：孟凡民[1] 张刃[1] 李庆利[1] 崔晓春[1] 

机构地区：[1]中国航空工业空气动力研究院,沈阳110034

出　　处：《实验流体力学》2015年第2期43-47,共5页Journal of Experiments in Fluid Mechanics

摘　　要：为满足未来我国先进飞行器的发展需求,我国将考虑建设大型跨声速风洞,提高风洞试验模拟精细化水平。而第二喉道作为风洞Ma数控制的有效手段,被认为是提升跨声速风洞能力的关键技术之一。本文首先通过CFD数值模拟发现了二喉道段流场在某些压比下存在不对称现象,然后,利用现有引导风洞,设计加工了Ma=0.7的带可变中心体的二喉道段进行验证试验。试验结果显示,当前室总压达到某一值时,二喉道段流场会出现不对称现象,并前传影响试验段流场品质。最后利用CFD手段给出了一种无不对称现象的新型二喉道设计。China will consider the construction of large transonic wind tunnels and develop fi-ner wind tunnel test simulation techniques to meet the needs of future advanced aircraft develop-ment.As an effective means to control the Mach number,the second throat is considered to be one of the key technologies to enhance the ability of transonic wind tunnel.In this paper,we i-dentify the asymmetric field flow in the second throat by the CFD simulation.Then we design and manufacture a new second throat section with variable center subject for the model wind tun-nel.The wind tunnel test results show that the asymmetriy field flow occurs in the second throat when the total pressure reaches a certain value,which can be forward transmitted to affect the quality of the test section flow.Finally,we design a new kind of second throat which would not generate the asymmetric field flow by the CFD method.

关 键 词：亚声速 中心体 第二喉道 不对称 数值模拟 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]