带襟、副翼三维机翼粘性绕流计算

摘要

The chimera embedding technique is presented to generate the grids for the configuration of a wing with control surfaces. It divides the whole region into many subdomains according to the wing, the aileron or the flaps, the cuts of the wing and the ends of the aileron or the flaps. The Renolds averaged Navier-Stokes equations and Johnson-King turbulence model are used for every subregion with the finite volume method.Through couple iterating, the solution of the whole flow field is obtained by exchanging information between subregions. The result of the delta wing with control surfaces shows that the results of the present method are in agreement with the experiment data very well.%运用嵌套网格方法严格考虑机翼切口和副翼、襟翼端面几何形状生成了合理的计算网格，并应用雷诺平均Navier-Stokes方程和Johnson-King湍流模型计算了带副翼三维机翼和带双襟翼三维机翼的粘性绕流。计算实践表明，用该方法可以很好地预计压力分布和最大升力