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基于5阶WENO格式结合AUSM+-up通量分裂方法编制密度基有限差分数值计算程序,并对NACA 65平面叶栅在不可压和亚音速工况下的流动进行三维大涡模拟研究,计算所得翼型表面时均压力系数分布与文献中实验结果符合较好,使数值算法和计算程序的可用性得到验证。大涡模拟获得了叶栅流道内瞬态流场的细节特征,体现了高分辨率格式捕捉精细流动结构的能力。本文工作为针对叶轮机械复杂可压缩内流问题进行更深入的高精度LES研究奠定了基础。
Based on the fifth-order WENO scheme combined with the AUSM + -up flux-splitting method, a numerical program for the numerical calculation of the density-based finite difference was developed. The 3D eddy simulation of NACA 65 plane cascade under incompressible and subsonic velocities was carried out. The distribution of time-averaged pressure coefficient of the surface is in good agreement with the experimental results in the literature, which verifies the usability of numerical algorithms and calculation programs. Large eddy simulation obtains the details of the transient flow field in the cascade runner, which shows the ability of high resolution format to capture the fine flow structure. This work lays the foundation for deeper and more accurate LES research on complex compressible internal flow problems of impeller machinery.