二维超音速喷管型线设计仿真研究  

Design and Numerical Simulation on the Two-Dimensional Supersonic Nozzle Profile

作　　者：刘晓东[1] 高丽敏[1] 李永增[1] 

机构地区：[1]西北工业大学,陕西西安710072

出　　处：《风机技术》2014年第4期25-29,48,共6页Chinese Journal of Turbomachinery

基　　金：西北工业大学基础研究基金(JC201141);新世纪优秀人才支持计划(NCET-10-0078)

摘　　要：采用计算软件FLUENT,对四种经典收缩段型线下的流场特性进行数值模拟,为选择超声速风洞收缩段的型线提供依据。基于特征线理论,利用解析法完成超音速喷管膨胀段型线设计,通过分析总压恢复系数及均匀度等流场参数,确定型线膨胀角角度及喷管长度。结果表明,收缩段型线选用双三次曲线,膨胀角度3.5°的情况下,超音速喷管出口达到了设计要求马赫数,并获得了较好的气流品质。In this paper, the research results about numerical simulation on the flow field of four classic convergent curves are gained by computational software FLUENT, which provides basis for selecting a kind of optimal curve to design the supersonic nozzle convergent profile. Based on the theory of characteristics line, the curve of supersonic nozzle expansion is designed with analytical method. Finally, comparing total pressure recovery coefficient and uniformity of flow field parameters, the angle of expansion curve and nozzle length are confirmed. The results show that exit velocity of the supersonic nozzle achieves the design requirements for Mach number and uniformity when Bipartite Cubic isthe method of the contraction profile and the angle of expansion profile is 3.5° .

关 键 词：二维喷管 特征线理论 数值仿真 

分 类 号：V211.754[航空宇航科学与技术—航空宇航推进理论与工程]