摘要
介绍了所设计的子弹-母弹气动干扰风洞实验研究方案的特点及实验装置,利用该装置进行了子弹对弹舱内压力分布影响的实验。实验结果表明:单独母弹弹舱内压力分布符合过渡式空腔流动规律,即在前端面后的区域为流动分离所形成的低压区(Cp<0),经Cp=0点过渡到Cp>0的区域;后端面对弹舱内流动起阻滞作用,在后端面左右拐角处存在流动缓慢的"死水区";母弹攻角对弹舱内的流动影响显著,正攻角起压缩作用,使前端面后的流动分离区内Cp>0降低,使分离区的纵向范围缩小,使Cp>0区域内的Cp值增大,负攻角起膨胀作用;子弹对母弹弹舱内的流动起压缩作用,当子弹为正攻角时,子弹对弹舱内流动的压缩作用降低。
A self-designed submunition-dispenser aerodynamic interference wind tunnel experiment device and the experiment program's feature are introduced.With the device the pressure distribution influence experiment of submunition to its cabin is conducted.The experiment results show that the cabin's pressure distribution represents the transitional-type cavity flow while there isn't submuntion,that is to say the region after the front-face of the cabin is a low pressure(Cp<0) area which caused by the flow separation,and translate to the region through the point Cp=0.The back-face blocks the flow in the cabin,so there is the slowly flow field namely 'dead zone' at the corner front back-face.The dispenser's angles of attack have an observably effect upon the flow field in the cabin,the positive angle of attack compress the flow,which make the pressure coefficient |Cp| of the flow separation area after the front-face decreased and the longitudinal flow separation region shrank;and that the positive angle of attack of the dispenser also makes the cabin's Cp value of the Cp>0 region increases.The dispenser's negative angle of attack makes the cabin's flow expanded.The effect of submunition to the cabin's flow is compressible but while the submunition is positive angle of attack relative to the dispenser,the compressive effect reduced.
出处
《空气动力学学报》
CSCD
北大核心
2012年第3期328-333,共6页
Acta Aerodynamica Sinica
基金
预研基金
关键词
子母弹
空腔流动
压力分布
气动干扰
风洞实验
submunition-dispenser
cavity flow
pressure distribution
aerodynamic interference
wind tunnel test
