低速旋转尾翼式弹箭气动特性数值研究

Research on Aerodynamic Characteristics of Missile With Fins Under Low-speed Rotation

为了研究低速旋转对尾翼式弹箭气动特性的影响,采用三维非定常N-S方程并结合滑移网格技术,在小攻角和全马赫数下,对某尾翼弹在低转速状态下的绕流流场进行了数值模拟。以美国陆-海军动导数计算标模验证该文算法的有效性。结果表明该方法有较高的精确度。由不同马赫数、转速和滚转角条件下的计算结果发现:纵向气动特性(即升力、阻力、俯仰力矩)不随转速而变化,平均滚转力矩系数和转速为定比例关系,平均马格努斯力系数随转速呈非线性变化,瞬时马格努斯力系数随滚转角呈正弦变化。

In order to research the effect of low speed rotation on aerodynamic characteristics of missile with fins,the flow field around the missile with fins under small attack angle and total Mach number was simulated by applying3D unsteady N-S equations and slide mesh technology.The Army-Navy Basic Finner Missile was used for verifying the validity of the numerical simulation method.The results show that this method has high accuracy.The results under different Mach numbers,rotation speed and roll angle show that the longitudinal aerodynamic characteristics(lift,drag,pitching moment)is independent of spin.The average rolling-moment-coefficient is contantly proportionate to rotation speed,and the average Magnus-force-coefficient exhibits a nonlinear change with the rotation speed.