三维机翼尾涡面卷曲的数值模拟

Numerical Simulation of 3D Foil with Trailing Vortex Sheet Roll-up

采用离散涡环法来模拟三维机翼的升力效应,机翼尾涡面由双曲四边形面元进行离散,每个面元上布置线性偶极子分布,由尾涡面上的运动学条件来确定三维涡面卷曲形状,在诱导速度计算中引入了非奇异化的光滑参数,数值模拟结果显示了本方法的有效性,与试验结果和其他数值方法相比是吻合的.

The Vortex Lattice Method is adopted to simulate the lift force effect of three dimensional foils,Trailing vortex surface behind the foil is discreted by a number of small hyperboloidal quadrilateral panels with the linear doublet distribution on each panel. The geometry of three dimension vortex sheet roll-up is determined by the kinematic condition on vortex sheet. The desingularization smoothing parameter is introduced in calculating the induced velocity. Numerical simulation result is shown to be efficient The tip vortex geometry is in satisfactory agreement with experimental data and other numerical result.