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A MIXED ELEMENT TYPE UNSTRUCTURED GRID METHOD FOR SIMULATING 3D TURBULENT FLOWS

机译:用于模拟3D湍流流动的混合元件型非结构化网格方法

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In this paper, a method is presented for the viscous flow simulations by solving the Navier-Stokes equations on three-dimensional mixed element type unstructured grids. Pirzadeh's advancing-layer method is modified to generate high quality mixed prismatic/pyramidal/tetrahedral element type 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 AUSM~+—up 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 assessments of the presented method are derived from the simulation of viscous flow problems around the ONERA M6 wing. DLR-F6 wing-body and DLR-F6 wing-body-pylon-nacelle configuration.
机译:在本文中,通过在三维混合元件类型非结构化网格上求解Navier-Stokes方程来提出一种粘性流动模拟的方法。 Pirizadeh的推进层方法被修改为在边界层区域产生高质量的混合棱柱形/金字塔型/四面体元件型非结构化网格,并且前进方法用于构建残余流动区域中的各向同性四面体网格。通过使用具有AUSM〜+ -UP方案和Spalart-Allmaras单一方程湍流模型的细胞居中的有限体积方法来解决三维Navier-Stokes方程。通过使用通量载体的一阶线性化和助焊剂jacobi基质的最大特征值分裂来构建的隐含高斯 - 赛德尔弛豫程序提前了。提出的方法的评估是从Onera M6翼周围的粘性流动问题的模拟来源的。 DLR-F6翼形和DLR-F6翼形 - 塔孔机舱配置。

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