适用于高速层流翼型的计算网格研究

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-w 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.