二维超音速喷管设计仿真研究  

Designing and numerical simulation on two dimensions supersonic nozzle

作　　者：张宏义[1] 张发启[1] 孙权[1] 

机构地区：[1]空军工程大学空军工程学院飞行器与动力工程系,西安710038

出　　处：《机械设计与制造》2011年第10期132-134,共3页Machinery Design & Manufacture

摘　　要：采用特征线理论设计二维超音速喷管型线,目的是产生超声速气流,用于开展和超声速流动相关的实验研究。采用采用维托辛斯基曲线经验公式对喷管收缩段进行设计,分别采用圆弧加直线和Folsch解析法对扩张初始段和终止段进行设计,得到位流曲线,再结合附面层影响进行修正,最后运用Fluent软件进行仿真验证型线,结果表明喷管出口流速达到了设计马赫数要求且流场较为均匀。Two-dimensional profile for a supersonic nozzle is designed by adopting theory of characteristics line,the purpose is to generate supersonic flow,supersonic flow for the development and experimental research related.By using empirical formula vito sienski curve,the nozzle contraction is designed,then the expansion for initial section and terminal section is designed by adopting arc added with straight line and Folsch circular plus linear analytical method respectively to get a bit stream curves.Furthermore modification is carried out combining with boundary layer effects.Finally the profile is simulated and rectified with Fluent software,which results show that exit velocity of the nozzle achieves the design requirements for mach number and the flow field is more uniform.

关 键 词：二元喷管 特征线理论 位流曲线 边界层 数值仿真 

分 类 号：TH16[机械工程—机械制造及自动化] V228.7[航空宇航科学与技术—飞行器设计]