细长体非对称涡控制影响因素分析

Numerical Study of Primary Factors of Asymmetric Vortices Control over Slender Body

为开展非对称涡主动流动控制技术在战术导弹气动设计领域应用研究,采用有限体积法求解N-S方程,数值模拟了细长体和微扰流块的超声速耦合流场。结果表明:微扰流块对细长体前体分离涡系起到增强和放大作用,使整个流场涡系严重不对称,并产生可控制的侧向力,侧向力的大小取决于背风区非对称涡系的位置和强度,受细长体自身气动外形及扰流块的大小、位置、形状和数量影响。

In order to research the application of asymmetric vortices control on tactical missile, the N-Sequations are solved using finite volume method and the numerical studies are performed for supersonic flow past a slender body equipped with miniature flow effectors. The results show that fore-body separation vortices can be boosted up by miniature flow effectors, which result in that the whole flow structure are asymmetric and the side forces induced are controllable, the magnitude of side forces are depended by the number, size, shape, axial location of the flow effectors and the configuration of the slender body.