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用涡格镜象数值解法计算了亚音速定常流中旋转弹在有俯仰及副翼偏转(或舵偏)的情况下,弧翼身组合体和直翼身组合体的气动导数。该方法是将弹翼按一定规律分成许多网格,每一网格内放置一个后掠马蹄涡和一个控制点,用一组离散马蹄涡来模拟具有攻角和弯度的弹翼,小块面元内应用儒可夫斯基定理。由位于弹翼弦平面的控制点应满足的弹翼绕流边界条件建立关于弹翼环量分布的线性方程组。与弹翼相连的弹身是圆柱体,弹身的作用是通过在柱体内布置如下的奇点来模拟:柱体内布置与弹翼马蹄涡系对应的镜象马蹄涡系;柱体表面分割成许多网格,每个网格中点(同时也是控制点)放置空间源(汇);如果弹身的攻角不为零,则在轴线上布置二维偶极子。上述奇点强度按柱体表面网格控制点必须满足法向诱导速度为零的边界条件来确定。
The aerodynamic derivative of the arc wing and straight wing combination was calculated by the numerical solution of the vortex grid mirror method under the condition of pitch and aileron deflection (or rudder deflection) in subsonic steady flow. The method divides the wing into a plurality of grids according to a certain rule. Each grid has a sweepback horseshoe vortex and a control point. A set of discrete horseshoe vortices are used to simulate the wing with the angle of attack and camber, Yuan Ruijinshi theorem. A linear system of equations about the amount distribution of the missile wing rings is established by the boundary condition of the missile ’s flow around the control point located at the chord plane of the missile. The body of the missile connected to the wing is a cylinder. The function of the body is simulated by arranging the following singularities in the cylinder: a mirror-like horseshoe vortex which corresponds to the horseshoe vortex of the wing is arranged in the cylinder; the surface of the cylinder is divided into Many meshes, each meshed mid-point (also a control point) places a spatial source (sink); if the body’s attack angle is non-zero, then a two-dimensional dipole is placed on the axis. The above-mentioned singularity strength is determined by the boundary condition that the control point of the grid surface of the cylinder must satisfy the normal induction speed to zero.