Numerical simulation of laminar separation bubble over 2d airfoil at low reynolds number 翼型低雷诺数层流分离泡数值研究
In this thesis , hypersonic sidewall compression inlet ' s self - starting characteristics are numerical simulated and tested . with increasing mach number of inflow gradually , the hypersonic sidewall compression inlets can self - start . compared with the hypersonic sidewall compression inlet starting directly , characteristics are different . moving cowl , decreasing interior contraction ratio also can realize the hypersonic sidewall compression inlet ' s self - starting because of separation bubble on sidewall spilling out 其次,在数值模拟结果的基础上,设计了实验模型和装置并在马赫3 . 85的风洞中进行了移动唇口板减小内收缩比实现侧压式进气道自起动的风洞实验,验证了数值模拟的结果。