2018年第7期（总第247期）
doi:10.3969/j.issn.10093230.2018.07.001
应用能源技术
高超声速风洞喷管型线设计
陈威男"，徐林”
（1.华中科技大学中欧清洁与可再生能源学院，武汉430070；
2.华中科技大学能源与动力工程学院，武汉430070）
摘要：高超声速飞行器在空间探索和国防领城受到了越来越广泛的关注。高超声速风洞是进行高超声速飞行器空气动力推进性能实验的关键设备，而喷管型线决定了实验区域流场的品质，是整个风洞系统中最关键的部件之一。文中详细论述了高超声速风洞喷管的型线设计方法，收缩投的型线设计采用维托辛斯基经验公式法，膨胀段型线的设计采用基于特征线法的 Sivells法，附面层修正采用线性修正法。利用MATLAB编程求解喷管膨胀段型线坐标时，将普朗特一麦耶角的反演公式应用于求特征线网格节点的马赫数，大大加快了设计收敛进程。最后用模拟仿真计算得到整个计算城内的马赫数分布，结果良好，喷管出口截面核心区内马赫数分布符合设计值并且分布均匀，认为本次设计结果能够满足相关要求。
关键词：高超声速风洞；喷管型线；反演公式；仿真模拟
中图分类号：V231.3
文献标志码：A
文章编号：10093230(2018)07-000104
ContourDesignofHypersonicWindTunnelNozzles
CHEN Wei - nan', XU Lin?
(1. China EU Institute for Clean and Renewable Energy,Huazhong University of Science and Technology(HUST),Wuhan 430070,China;2.StateKeyLaboratory of Coal Combustion,
School of Energy and Power Engineering,HUST, Wuhan 430070,China)
Abstract:Hypersonic vehicles have attracted more and more attention in the field of space exploration and national defense. Hypersonic wind tunnel is the key equipment for aerodynamic propulsion experiment of hypersonic vehicle, and the contour of a nozzle determines the quality of the flow field in the experimental area, so the nozzle is one of the most critical parts of the whole wind tunnel system. This paper discusses the design method of the contour of hypersonic wind tunnel nozzles.The profile of the contraction
section is designed by applying the Vito Shinseki empirical
formula, and the Sivells method which is bas profile of the diver
The coordinates of the profile formula of thePrandtlM
nodes, which greatly of the whole co
Mach number in the distribution is uniform
otthe
the
nethod of characteristics is used to design the
ection method.
MATLAB and the inversion
of the characteristic grid
umberdistribution The distribution of
t of the design value and the
sults can meet the relevant requirements.
nel;Nozzle contour;Inversion formula;Simulation
Key words: Hypersonic wind tunn
0
引言
高超声速飞行器技术是未来航空航天技术新收稿日期：20180322
修订日期：20180511
作者简介：陈威男，华中科技大学中欧清洁与可再生能源学院
万方数据
1
的制高点，具有战略性、前瞻性、标志性和带动性1]。通常把马赫数大于6的飞行器叫高超声速飞行器。高超声速飞行器的开发和性能测试需要大型实验设备一高超声速风洞来提供相应的模拟