论文部分内容阅读
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 flow field inside the nozzle and the flow field around the missile were simulated numerically using the second-order accuracy Roe scheme, and the three-dimensional Navier-Stokes equations were discretized. The k-ω turbulence model was used to simulate the turbulent flow. The lift coefficient, drag coefficient and pitch moment coefficient of the missile were obtained by dimensionless integration of wall pressure and friction force, and the effect of vector jet on aerodynamic load was analyzed. The secondary pressure ratio (SPR) increases linearly and increases linearly. At different flight velocities and angles of attack, the aerodynamic loads vary with the SPR.