型面旋转变马赫数风洞喷管的优化设计  

Optimization Design of Variable Mach Number Wind Tunnel Nozzle by Rotating Profile

作　　者：范志鹏[1] 徐惊雷[1] 吕郑[1] 莫建伟[1] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《航空学报》2014年第5期1216-1225,共10页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(90916023;51176075)~~

摘　　要：型面旋转的变马赫数可调风洞喷管因其能够实现出口马赫数的连续快速变化、调节容易和流场品质较好等优点,成为目前地面变马赫数风洞研究的热点.将出口马赫数范围为2.0～4.0的变马赫数风洞喷管作为研究对象,基于iSIGHT和Fluent等软件搭建了适于该风洞喷管的优化设计平台,研究了型线设计中设计点马赫数、初始膨胀线和附面层修正量等因素对变马赫数出口流场的影响,应用NSGAⅡ算法在依据试验设计点所构建的Kriging近似模型上搜索,得到最优的风洞喷管基准型线,并对该基准型线进行二维、三维数值仿真校核,结果显示：通过旋转优选得到的基准型线能够得到马赫数范围为2.0～4.0的变马赫数出口流场,且流场均匀性基本满足固定型面、单设计点风洞喷管的国军标（GJB-1179-91）合格指标,为变马赫数可调风洞喷管在变马赫数风洞中的实际应用奠定了良好的基础.The study of variable Mach number wind tunnel nozzle with good performance and easy adjustment,which can generate fast response on the exit Mach number by rotating the tunnel profile,is now a focus of research.In this paper,corresponding to the wind tunnel nozzle with exit Mach numbers varying from 2.0 to 4.0,an optimization design platform based on the iSIGHT and Fluent softwares is built to find out the effect of the design factors on the exit flowfield,including the design Mach number,initial expansion line,boundary layer correction,etc.In order to obtain the best baseline profile,the NSGA Ⅱ algorithm is used to research the Kriging model approximation constructed based on the experimental design points.Then,2D and 3D numerical simulations are implemented to verify the baseline profile’s performance.It is shown that,uniformity of the exit flowfield with Mach numbers varying from 2.0 to 4.0 by rotating the baseline profile can satisfy the requirements of the Military Standard of China （GJB-1179-91） for the wind tunnel nozzle,which is originally set for the Mach number uniformity at the exit of the wind tunnel nozzle designed on the single design point with a fixed profile.The present work has laid a solid foundation for the application of the variable Mach number wind tunnel in future.

关 键 词：风洞 喷管 变马赫数 型面旋转 优化设计 数值仿真 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]