作　　者： ; ; ; ;

机构地区： 西北工业大学动力与能源学院翼型叶栅空气动力学国防科技重点实验室

出　　处： 《西北工业大学学报》 2006年第1期84-88,共5页

摘　　要： 运用非结构混合网格上N S方程的求解技术对三维舵面的粘性绕流进行了计算研究。在物面粘性作用区,运用改进的推进层方法生成三棱柱、金字塔和四面体型混合网格;在其它流动区域采用阵面推进方法生成四面体网格。采用基于重构中心格式的格心有限体积法和SPALART-A LLM ARAS一方程湍流模型对N S方程进行空间离散,运用通量线化假设和最大特征值方法进行雅可比矩阵分裂来实现隐式高斯-赛德尔时间迭代。以某带舵面偏转的机翼模型为数值算例,系统地计算和分析了迎角、舵偏角及马赫数对舵面气动特性和舵面流动分离的影响,并将计算得到的舵面铰链力矩与实验结果进行了对比验证。数值算例表明:该方法可以为三维舵面气动力和铰链力矩的计算与分析提供有效的数值工具。 The advancing-layer method is modified to generate high quality mixed （prismatic/pyramid/ tetrahedral） element unstructured grids in boundary-layer region and advancing-front method is used to construct isotropic tetrahedral grids in the residual flow region. Three-dimensional Navier-Stokes equations are solved by using a cell centered finite-volume method with central difference scheme and Spalart-Allmaras one-equation turbulence model. Time is advanced by an implicit Gauss-Seidel relaxation procedure, which is constructed by using the first-order linearizing of flux vector and the maximal eigenvalue splitting of flux Jacobi matrix. The simulation results of complex viscous flow around a 3D model wing with control surface are presented. The influences of attack angle, control surface deflection angle and Mach number on the flow separation are systematically investigated. Moreover, the comparison between the moments of gamel obtained by numerical simulations with those obtained by wind tunnel tests is presented; it should be pointed out that test data for one type of balance show noticeable difference from those for another type of balance. The computed results agree fairly well with the experimental data, which indicates that the viscous flow solver of this paper is useful in simulating the massively separated flows around 3D wing with deflection of control surface.

关 键 词： 非结构混合网格 隐式算法 方程 舵面

领　　域： [航空宇航科学与技术] [航空宇航科学技术]