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针对飞机设计对于减小诱导阻力的需求,结合升力线理论中三维机翼诱导阻力的相关研究,提出机翼的几何扭转设计方法.此设计方法以总升力、机翼平面形状、翼型气动特性为输入参数,以机翼的几何扭转为输出.在低速情况下,利用此方法得到的机翼具有椭圆形升力分布,从而具有最小的诱导阻力.采用远场法计算诱导阻力,应用参数化方法和CATIA实现机翼的自动生成,应用网格生成工具ICEM的脚本语言实现气动网格自动生成,应用MATLAB的符号运算功能编制程序.该设计方法适用于低速有粘流中平直翼的几何扭转设计,算例的CFD(Computational Fluid Dynamics)计算结果表明:利用该方法设计的机翼展向升力分布为椭圆,并能有效降低机翼的诱导阻力.
Aiming at the demand of aircraft design to reduce the induced resistance and the related research on induced resistance of the three-dimensional wing in lift line theory, the design method of geometric torsion of the wing is proposed. The design method is based on the total lift, wing plane shape, aerodynamic characteristics In order to input the parameters, the geometrical twist of the wing is taken as the output.With the low speed, the wing obtained by this method has the elliptical lift distribution and thus has the minimum induced resistance.The far-field method is used to calculate the induced resistance and the parameterized method And CATIA to realize the automatic generation of the wings.Automatic generation of the aerodynamic mesh is realized by using the scripting language of ICEM, and MATLAB is used to program the symbolic operation function.The design method is suitable for geometric torsion The CFD (Computational Fluid Dynamics) results of the design and the example show that the wing structure designed by this method has an elliptical lift distribution and effectively reduces the induced resistance of the wing.