摘要
用数值方法模拟了激波诱导矢量喷流时喷管内流场和导弹绕流流场.采用二阶精度Roe格式对三维Navier-Stokes方程进行了离散,利用k-ω湍流模型模拟了湍流流动.通过对壁面压力和摩擦力积分并无量纲化得到了导弹的升力系数、阻力系数和俯仰力矩系数,分析了矢量喷流对气动载荷的影响.结果表明,矢量偏角随次流与主流压力比(Secondary Pressure Ratio,SPR)增大而线性增大;在不同飞行速度和攻角下,气动载荷随SPR的变化而呈现不同的变化规律.
The inner flowfield of nozzle and the flow over missile affected by shock vectoring jet flow are simulated numerically.Roe＇s scheme is used to discretize three-dimensional Navier-Stokes equations,and the k-ω turbulent model is used to simulate turbulent flow.The pressure and friction distributions on the wall are numerically integrated and make dimensionless to compute the lift coefficient,drag coefficient and pitch moment coefficient,and the influence on these aerodynamic load parameters by vectoring jet are analyzed.Results indicate that vectoring angle increases linearly with the increasing of SPR,and the aerodynamic load parameters vary with SPR under different flying speed and attack angle.
出处
《战术导弹技术》
2011年第4期56-60,共5页
Tactical Missile Technology
关键词
导弹
推力矢量
气动载荷
数值模拟
missile
thrust vectoring
aerodynamic load
numerical simulation
