摘要
Abstract
Due to the influence of sideslip angle,attack angle and roll angle,the oblique flow of canard-type missile with large length-diameter ratio generated by the canard rudder is very serious when the bank-to-turn control is carried out.Additional out-of-plane forces and moments of the missile may be caused since the flow around the tail and body is asymmetric.Therefore,in order to study the effect of sideslip angle on the aerodynamic characteristics of missiles with large length-diameter ratio,hexahedral polyhedral grids of the flow field domain were generated.Numerical simulation was conducted on the aerodynamic characteristics of canard shaped projectiles at different attack angles,Mach numbers,rudder angles,and sideslip angles.The variation law of the aerodynamic characteristic,streamline,vorticity,and pressure cloud maps of the projectiles were obtained.Wind tunnel experiments of the missile was carried out.The experimental results were compared with simulation data,which verified the feasibility of the CFD method.The research shows that the downwash flow of the canard-rudder is shifted to the side of the affecting by the body sideslip angle and long missile body.The washing flow of the canard rudder shows little effect on the tail.With the increases of local angle of attack of the tail,the normal force of the tail increases too.Therefore,the pressure center of the missile shifts back,the equilibrium angle of attack decreases,the static stability margin becomes larger,and the pitch maneuvering efficiency of the missile decreases.While,the local angle of attack of the tail and the normal force of the arrow are reduced in a few cases,result in reducing the static stability and improving the maneuvering efficiency of the arrow.关键词
侧滑角/数值模拟/风洞实验/鸭舵布局/气动特性/大长径比Key words
sideslip angle/numerical simulation/wind-tunnel test/canard configuration/aerodynamic characteristics/large length-diameter ratio分类
军事科技
