CAJ | 학술논문

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。
이용FLUENT연건대모도탄말제도상태기동특성진행수치계산。장말제도상태각마혁수、공각하법향력계수、축향력계수、부앙력구계수、압심계수여기본형기동수거진행분석대비，병분석료도인두、전람조대도탄기동특성적영향。결과표명，재아성속화과성속상태，도인두여전람조대도탄종향기동특성영향교소，대령측활각정황하적횡향기동특성영향교대，대류장적분석지출，류동불대칭성적가극시조성차충기동특성변화적주요원인。
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.