高超声速风洞喷管型线设计  

Contour Design of Hypersonic Wind Tunnel Nozzles

作　　者：陈威男 徐林[2] CHEN Wei-nan;XU Lin(China-EU Institute for Clean and Renewable Energy,Huazhong University of Science and Technology（HUST）,Wuhan 430070,China;State Key Laboratory of Coal Combustion,School of Energy and Power Engineering,HUST,Wuhan 430070,China)

机构地区：[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

出　　处：《应用能源技术》2018年第7期1-4,共4页Applied Energy Technology

摘　　要：高超声速飞行器在空间探索和国防领域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,收缩段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-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域内的马赫数分布,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。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 aerodynamie 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 based on the method of characteristics is used to design the profile of the divergent section. The boundary layer is corrected applying linear correction method. The coordinates of the profile of the divergent section is solved applying MATLAB and the inversion formala of the Prandtl Meyer angle is applied to solve the Maeh number of the characteristic grid noddes, which greatly acelerate the convergence of tile design. Finally, tile Maoh number distrihution of the whole eomputational domain is obtained by simulation. Tile result is good. The distribution of Maeh number in the core area of the nozzle outlet meets the requirement of the design value and the distribution is uniform. It is considered that the design results can meet the relevant requirements.

关 键 词：高超声速风洞 喷管型线 反演公式 仿真模拟 

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]