In this paper, the numerical simulation on the aerodynamic configuration of a missile in terminal guiding state,which adds the seeker and cable protuberance to the basic state,is carried out by FLUENT software. The aerodynamic characteristics of terminal guiding state are analyzed and compared with the basic state. The contributions of seeker and cable protuberance to the aerodynamic configuration of a missile are studied. The results reveal that in subsonic and transonic status, the terminal guiding system has little influence on longitudinal aerodynamic performance, but affects the lateral aerodynamic characteristics greatly under zero yaw angle. The investigation on the flow field concluded that the growing asymmetry of the flow is the main reason which leads to the changes in the aerodynamic characteristics.%利用FLUENT软件对某导弹末制导状态气动特性进行数值计算。将末制导状态各马赫数、攻角下法向力系数、轴向力系数、俯仰力矩系数、压心系数与基本型气动数据进行分析对比，并分析了导引头、电缆罩对导弹气动特性的影响。结果表明，在亚声速和跨声速状态，导引头与电缆罩对导弹纵向气动特性影响较小，对零侧滑角情况下的横向气动特性影响较大，对流场的分析指出，流动不对称性的加剧是造成此种气动特性变化的主要原因。
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