摘要
采用风洞试验和数值模拟相结合的方法对超音速子母弹分离干扰流场特性进行了研究。对比数值模拟与试验研究结果表明,结合k-ωSST两方程湍流模型求解雷诺平均N-S方程,并以AUSM+作为离散格式的数值方法,可较为细致地模拟子母弹分离干扰流场。通过对子母弹特定状态干扰流场结构的分析和对其流动机理的探讨,发现由于激波相互干扰使弹体表面压力分布多变、子弹攻角增大时纵向干扰量大影响子弹分离姿态。本文的工作为进一步研究子母弹分离干扰流场流动机理奠定了基础。
For the interference flow field on separation of supersonic dispenser, a novel method using numerical simulation and experiment is proposed in this paper. The computational solutions are well consistent with the experimental results, so the flow characteristics can be simulated satisfactorily by the method of Reynolds-averaged Navier-Stokes equations, and splitting scheme AUSM+ Analysing flow field structure specific condition, pressure characteristics is found on surface by shock disturbance, aerodynamic parameters of submunition are interfered by shock of carrier. The flow field principle is revealed. The vital reference is provided for investigating separation interference flow field of supersonic dispenser.
出处
《空气动力学学报》
EI
CSCD
北大核心
2010年第3期310-315,共6页
Acta Aerodynamica Sinica
关键词
子母弹
干扰流场
数值模拟
风洞试验
cluster munition
interference flow field
numerical simulation
wind tunnel test