摘要
本文应用激光蒸汽屏方法揭示了在跨超声速时，战术弹模型大攻角下的空间流态，同时，分析了旋涡结构和涡系干扰。指出了在亚声速和跨声速时涡的结构随来流Ｍ数的变化不明显；而光弹身模型在Ｍ＝０．６～０．９时，涡系均为非对称，是由于尖拱形头部的脱体激波及大攻角时流动的非稳定性和气体压缩性共同作用的结果，当α≥１６°，Ｍ≥１．０时，涡系均为对称的。这些涡系的对称性和非对称性影响着弹体的空气动力学特性。
This paper reveals spatial flow tactical missile by method of laser vapor screen visualization at transonic and supersonic speeds,at same time,analyzes the vortex structure and the interactions of vortex vortex and vortex shock.With the increment of Mach number and angle of attack the structure does not change evidently.There are quite asymmetric vortices over body alone model at Mach number from 0.6 to 0.9,because of forebody shock were of ogive cylinder,unstability flow at high angle of attack and compressibility.However,vortex structure is symmetric at α≥16°,M ≥1.0 difference of vortex structure effect areodynamic characteristic of tactical missile.
出处
《空气动力学学报》
CSCD
北大核心
1998年第3期325-330,共6页
Acta Aerodynamica Sinica
关键词
战术导弹
激光蒸汽屏
流动显示
跨超音速
tactical missile
laser
vapor screen
flow visualization
vortex
