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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 carry out the asymmetric eddy current active flow control technology in the field of tactical missile aerodynamic design, the finite volume method is used to solve the N-S equation, and the supersonic coupled flow field is numerically simulated. The results show that the perturbation flow block enhances and amplifies the separation vortex system of the slender body, which makes the vortex system of the whole flow field seriously asymmetric and produces a controllable lateral force. The magnitude of the lateral force depends on the leeward The location and intensity of non-symmetrical vortex systems in a zone are influenced by the aerodynamic shape of the slender body and the size, location, shape and number of spoiler blocks.