摘要
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.
出处
《武汉理工大学学报（交通科学与工程版）》
2005年第6期844-847,共4页
Journal of Wuhan University of Technology（Transportation Science & Engineering）
基金
湖北省行业联合攻关项目资助(批准号:95-05-52-04-02)
关键词
机翼
涡面卷曲
涡环法
foil
vortex sheet roll-up
vortex lattice method
