旋转式尾翼弹箭气动特性仿真计算OA北大核心CSTPCD

In order to study the aerodynamic characteristics of the missiles with tail fins,simulation was conducted to study the unsteady flow-field of the missiles with rotating tail fins based on sliding mesh method.The numerical simulation method adopted in this paper was verified by the wind tunnel experimental results of army-navy finner(ANF)standard model.Taking a certain cross-shaped layout tail-fin missile as the research object,the variation laws and influencing mechanisms of various aerodynamic-characteristic-parameters at different Ma(Ma=0.9-2.0),attack angles(2 °,4 °),rotation speeds(π rad/s,2π rad/s,4π rad/s),and tail-fin inclination angles(0°,1°,2°),were analyzed.The calculation results show that the rotation speed has little effect on the longitudinal aerodynamic characteristics(drag,lift,pitch moment characteristics)of the missile,mainly affecting the roll characteristics and Magnus effect.The inclination angle of the tail fin has little effect on the lift characteristics parameters and pitch moment characteristics of the missile,mainly affecting the drag,roll characteristics and Magnus effect.The resistance characteristics parameters and lift characteristics parameters of the missile show periodic variation during missile rotating around its longitudinal axis(0°-360°),and the instantaneous coefficient of lift and drag is the smallest when the missile rotates to 45°.The body is the dominant factor in generating the resistance characteristic(about 85％).The contribution of the body and tail to the lift characteristics is basically about 50％each.Therefore,in the design process of the projectile and arrow,attention should be paid to the advantages and disadvantages of the fin cant angle and rotation speed,and a suitable oblique angle should be selected.