摘要
针对结构网格很难处理复杂外形和非结构网格无法计算具有边界层的粘性流动的缺点,发展了基于混合网格格点的隐式算法,成功地解决了在工程应用中难于处理的复杂外形粘性流场计算和效率问题。同时针对大规模的工程问题,发展了基于MPI通信技术的染色分层通讯并行计算方法。其中空间离散采用基于Roe格式发展的三阶迎风HLLEW(Harten-Lax-Van Leer-Einfeldt-Wada)或AUSM格式,湍流模型采用k??两方程湍流模型,时间推进考虑到LU-SGS并行等效较困难则采用基于DP-LUR(Data-Parallel Lower-Upper Relaxation)格式的隐式算法,计算CFL数可取到105量级,从2个到128个CPU的并行加速效率都保持在90%以上,大大提高了计算效率。算例对标模M6机翼模型流场进行计算,验证了方法的可靠性;然后对标模DLR-F6翼身组合体进行混合网格粘性与无粘计算结果进行比较,进一步验证混合网格方法;最后计算了DLR-WBNP外挂发动机翼身组合体模型,准确模拟了外挂和超临界机翼的相互干扰流动问题,采用4 CPU 16 CORE到24 CPU 96 CORE,2000步计算时间都不超过3小时。为民机跨声速气动弹性分析的计算效率提升提供了基本的数值模拟工具。
To overcome the disadvantages that the complex shapes are difficult to generate the structured grid and the unstructured grid could not resolve the wall boundary layers for viscous flows,an implicit parallel computing method based on the Navier-Stokes equations with hybrid grids is studied.Parallel computing method based on coloration and packet communication using MPI is developed to solve the engineering problems with high computational cost.In the spatial discretization,the HLLEW（Harten-Lax-Van Leer-Einfeldt-Wada） and AUSM schemes are applied,and two equations turbulence models are used for the simulation of turbulent flows.The implicit time-marching method using DP-LUR（Data-Parallel Lower-Upper-Relaxation） is considered to improve the parallel computation.The three standard examples,containing the M6 model wing,the DLR-F6 wing-body combination and the DLR-WBNP wing-body combination,are simulated to validate the developed code through the comparisons of inviscid and viscous numerical results and wind tunnel experiments.The developed method can be used for the investigation of transonic computational aeroelasticity with high efficiency.
出处
《应用力学学报》
CAS
CSCD
北大核心
2011年第3期211-218,323,共8页
Chinese Journal of Applied Mechanics
