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本文从亚音速小扰动位势方程出发,给出了计算任意复杂组合体表面压力分布和纵向气动力特性的基本解的数值计算方法。把全机表面划分成许多网格,在每个网格上布置基本解以模拟物体,用物面上没有法向气流穿透的边界条件决定基本解的未知强度,从而计算出物面压力系数,积分出总气动力特性。该方法适用于任意形状的机身及任意平面形状、任意厚度、弯度和扭转分布的机翼(尾翼),机翼(尾翼)可以带有两段后缘操纵面。为降低对电子计算机存贮量、速度和稳定时间的要求,本方法采用了机翼、机身、尾翼部件之间的循环迭代求解。
In this paper, based on the small subsonic perturbation potential equation, a numerical method to calculate the fundamental pressure and surface aerodynamic characteristics of any complex assembly is given. The whole surface is divided into many grids, the basic solution is arranged on each grid to simulate the object, and the boundary conditions without the normal airflow penetrating on the object surface determine the unknown intensity of the basic solution to calculate the surface pressure coefficient , Points out the total aerodynamic characteristics. The method is suitable for any shape of the fuselage and arbitrary planar shape, arbitrary thickness, curvature and torsion distribution of the wing (tail), wing (tail) can be with two trailing edge control surface. In order to reduce the requirements for computer storage, speed and stability time, this method uses iterative iteration of the airfoil, fuselage, and tail components.