二维超音速喷管型线设计仿真研究

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。

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

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° .