适用于高速层流翼型的计算网格研究  

Research on the computing grid of high speed laminar airfoil

作　　者：赵欢[1] 高正红[1] 王超[1] 高原[1] 

机构地区：[1]西北工业大学,西安710072

出　　处：《应用力学学报》2018年第2期351-357,共7页Chinese Journal of Applied Mechanics

摘　　要：高速层流翼型计算的敏感性在于转捩位置的判定与后缘压缩流的捕捉,其气动力系数和流场计算精度受计算网格影响很大。本文针对高速层流翼型流场计算的特点,考虑计算网格的关键影响,提出了影响近壁网格分布和远场网格分布的关键参数,并通过优化研究找出了能显著提高计算精度的网格分布要求。计算结果表明,对基于SST k-ω的γ-Re_(θt)转捩模型RANS数值求解方式,优化网格的网格量(9.6万)在相对于标准网格的网格量(8万)仅增加20%的情况下,显著提高了高速层流翼型LRN1015等的气动特性数值模拟精度,有利于层流翼型的设计与分析。The sensitivity of high speed laminar airfoils computation lies on the accurate computation of transition location and pressure recovery region, and the computing grid has a great effect on the numerical precision of aerodynamic force coefficients and flow field of high speed laminar airfoils. In terms of the computing characteristics of high speed laminar airfoil, and considering the critical impact of computing grid on numerical precision, some critical factors which affect the distributions of near-wall grid and far-field grid are proposed.Some optimization methods are used to find out the proper values of these critical factors. It is shown by the computational results that by the γ-Re_(θt) transition model which is combined with the shear stress transport(SST)k-ω turbulence model, optimized grid significantly improves the numerical precision with only a 20% increase of grid number(96000) of optimized grid relative to that(80000) of normal grid. The proposed methods contribute to the design and analysis of laminar airfoil.

关 键 词：层流翼型 近壁网格 远场网格 优化网格 数值精度 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]