基于预处理的低速小展弦比机翼数值模拟

Numerical Simulation of Low Speed Flow Around Low Aspect Ratio Wings Using Preconditioning Techniques

以雷诺平均的Navier-Stokes方程为基础,应用非结构混合网格技术,基于有限体积的时间推进预处理方法,对小展弦比机翼的低速流动进行了数值模拟。其中对流项的离散应用了基于Roe的Riemann近似解迎风格式,时间离散应用了基于LU-SGS的隐式格式。为描述湍流流动,采用了Spalart-Allmaras一方程湍流模型。为了验证本文方法对低速小展弦比机翼粘性流动的数值分析效果,对几个不同展弦比的机翼进行了数值模拟。本文的数值结果与文献的实验数据基本一致,表明本文方法能够准确模拟小展弦比机翼在低速流动时机翼的展弦比对其气动特性的影响。

Based on the Reynolds-averaged Navier-Stokes equation the unstruceural hybrid grids are applied. Based on the time-derivative proconditioned method, the low speed aerodynamic propertics of low-aspect-ratio wing are numerically simulated. Among them, the upwinding schemes based on Roe＇s approximate Riemann solver is applied to discretization of the convective term. The implicit lower-upper symmetric gauss-seidel（LU-SGS） algorithm is applied to time discretization. The Spalart-Allmaras oneequation turbulence model is used to simulate turbulent-flow problem. Numerical results for a low-aspect-ratio wing is in agreement with the experimental data. The result indicates that the approach proposed can simulate the effect of the aspect ratio on aerodynamic character of low-aspect-ratio wings for the low speed flow.