亚声速外流场关键仿真参数与数值精度的相关性分析  

Correlation Analysis between Key Simulation Parameters and Numerical Accuracy in Subsonic External Flow Field

作　　者：杨路 王胜和 权冰娥 YANG Lu;WANG Shenghe;QUAN Binge(Anhui Police College,Department of Public Security Technology,Hefei,Anhui 230000)

机构地区：[1]安徽公安学院公安科技系,安徽合肥230000

出　　处：《绵阳师范学院学报》2024年第8期16-24,共9页Journal of Mianyang Teachers＇ College

基　　金：安徽省自然科学重点项目(2023AH053014);校级优秀科研创新团队项目(2023GADT06)。

摘　　要：基于风洞试验数据计算了压力系数、阻力系数和升力系数的误差率,详细分析了上述参数与数值精度的相关性.数值结果表明,不合适的后缘翼型形状会带来最大的数值精度下降幅值,达到28.20%,应优先采用尖后缘翼型.尖后缘翼型建模方法的选择则取决于所采用的建模数据点数量. Airfoil tools提供的建模数据点数量与数值精度之间存在负相关的关系,但是NACA4提供的建模数据点不存在类似的关系,并且前者提供的数据点的数值性能优于后者,可带来8.80%的精度提升幅值.对远场距离和湍流模型,在亚声速外流场的建议取值分别是20 L和SST k-omega.In this paper,based on the wind tunnel experimental data,the error ratios of pressure coefficient,drag coefficient and lift coefficient are calculated,and the relationship between the above parameters and numerical accuracy is analyzed in detail.Numerical results show that the improper trailing edge shape would bring the greatest amplitude of numerical accuracy reduction,reaching 28.20%,and the sharp trailing edge is suggested.The selec-tion of modeling method for the sharp trailing edge depends on the number of adopted data points.There exists a negative correlation between the data points number provided by Airfoil tools and the numerical accuracy,but there is no similar relationship between the modeling data points provided by NACA4,and the numerical performance of data points provided by the former is better than that of the latter,resulting in an 8.80%increase in calculation accuracy.For the far field distance and turbulence model,the recommended values for the subsonic external flow field are 20 L and SST k-omega,respectively.

关 键 词：亚声速外流场 NACA0012翼型 仿真参数 预示精度 

分 类 号：TP39[自动化与计算机技术—计算机应用技术]