论文部分内容阅读
本文旨在对高超声速发动机进气的流场进行分析、研究,并利用CFD软件技术在设备条件有限的情况下对该高超声速进气道进行零攻角时的状态进行三维流场的数值模拟,给出流场的速度矢量图、压力等值线图、以及压力分布图。分析在不同网格密度下的进气道模型在同一流场条件下所获得的结果有何差异。
The purpose of this paper is to analyze and study the flow field of the hypersonic engine intake and use CFD software to simulate the three-dimensional flow field of the hypersonic inlet at zero angle of attack with limited equipment conditions Gives the velocity vector of the flow field, the pressure contour map, and the pressure profile. Analyze the difference of the results obtained under the same flow field with the inlet model at different grid densities.