马赫数2～4连续可调风洞数值模拟及静态标定试验  

Numerical simulation and experimental calibration of continuously adjustable wind tunnel with Mach number 2 to 4

作　　者：齐伟呈 徐惊雷[1] 范志鹏[1] 莫建伟[1] 唐兰[1] 

机构地区：[1]南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室,南京210016

出　　处：《航空学报》2017年第1期86-94,共9页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(50876042;90916032;11672346)~~

摘　　要：型面旋转连续可调风洞可以获得出口马赫数连续变化的出口流场,其结构简单、易于调节、响应迅速,成为目前国内外的研究热点,具有很好的发展前景。本文针对某优化设计的出口马赫数2~4的变马赫数风洞喷管,进行了全流场三维数值仿真校核,并进行了风洞流场静态标定试验,获得了该连续可调风洞在不同马赫数下的流场品质及流场均匀区大小。结果显示:该连续可调风洞在马赫数2~4下的出口流场均匀性良好,流场品质满足固定几何风洞流场的国军标要求;试验得到的不同马赫数工况下均匀区大小均大于理想菱形区的2/3,均匀区马赫数标准差在马赫数2~3工况下小于0.01,在马赫数3.5工况下为0.013 6,说明该连续可调风洞可以实现马赫数的连续变化,且具有良好的流场品质,可用于后续的风洞试验。The study of variable Mach number wind tunnel nozzle with good performance,simple structure and easy adjustment,which can generate fast response on the exit Mach number by rotating the tunnel profile,is now a focus of research and has very good prospects for development.For the profile rotating wind tunnel nozzle with Mach number varying from 2to4 obtained by optimization design,3Dnumerical simulation and experimental calibration for the flow field of the wind tunnel have been conducted.The size of the real uniform region and the Mach number standard deviation in the condition of different Mach numbers are obtained.Experimental results show that the profile rotating wind tunnel can continuously change the wind tunnel Mach number from 2to 4,and the uniformity of the flow field is good,which even can meet up the requirement of the National Military Standard of China for a fixed geometry wind tunnel nozzle.The size of the real uniform region is larger than2/3of the ideal diamond region under the different Mach conditions.The Mach number standard deviations in the uniform region are less than 0.01 for Mach number 2to 3,and for Mach number 3.5is 0.013 6.It is shown that the wind tunnel can realize the continuous variation of Mach number with a good performance.Therefore,it can be used in the future for wind tunnel test.

关 键 词：连续可调 型面旋转 标定试验 流场品质 风洞 

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]