摘要
采用中心有限体积法求解Navier Stokes方程组 ,利用点对点搭接及面搭接多块网格技术成功地进行了多段翼型和存在外形间断 (剪刀差 )的带操纵面三维机翼的网格生成及粘性绕流流场数值计算 ,使用重叠面积加权插值及Ramshaw算法实现了面搭接的多块网格之间的信息传递并保证了通量守恒 ,并将流场计算结果与实验数据进行了对比 .
Because of the complexities in both configurations and flow phenomena,there are great difficulties in the numerical simulation of flow about wing with lift\|enhancing devices and control surfaces.By using cell\|centered finite volume method,it deals with Renolds\|averaged Navier\|Stokes equations on multi\|block structural grids generated by elliptic method.Two kinds of patching schemes,point\|to\|point and patch\|on\|common\|surface,are employed to establish the information exchange among blocks.In the later one,the overlap cell area weighted interpolation is used to guarantee the conservation.Ramshaw algorithm is also used to pre\|determine the overlap areas.Flow fields about multi\|element airfoils and delta wing with deflected flap are computed with the present method.Numerical results are all in good agreement with experiment data.Flow field visualization shows the present method has good resolution in flow details.
出处
《计算物理》
CSCD
北大核心
2001年第4期318-324,共7页
Chinese Journal of Computational Physics
