不可压缩翼型绕流数值研究

Numerical investigation of impressible turbulent flows past airfoils

使用标准k-ω模型及与色散模型相耦合的k-ω模型分别计算了NACA0012翼型和NACA 4412翼型的低速绕流问题.NACA 0012翼型计算了其来流雷诺数为2.88×106,攻角从0°到15°范围内的流动结构、翼型表面压力分布和升力、阻力特性;NACA 4412翼型计算了临界雷诺数为1.52×106,攻角为13.87°时的流动分离和翼型表面压力系数,并与实验数据进行对比.结果表明:在同等条件下,使用与色散模型相耦合的k-ω模型计算得到的NACA 0012翼型的升力和阻力系数比标准k-ω模型提高精度约5%,NACA 4412翼型的表面压力系数精度提高了约3%,进一步验证了其可信性,可将其进一步应用到低速飞行器的气动计算中.

The standard k-ω model and the k-ω model coupled with dispersion model were computed for turbulent flow over two airfoils, NACA 0012 and NACA 4412. The flow characteristics on the surface of the NACA 0012 airfoil were analyzed in detail under a typical Reynolds number of 2.88×106 and attack angle from 0° to 15° including pressure coefficient, lift coefficient and drag coefficient; the flow characteristics on the surface of the NACA 4412 airfoil were analyzed in detail under a typical Reynolds number of 1.52×106 and attack angle of 13.87° including the flow separation and pressure coefficient, and then compared with the experiment data. Under the same condition, the new model improved the accuracy of about 5% than the standard k-ω model when calculating the lift coefficient of NACA 0012, and improved the accuracy of about 3% than the standard k-ω model when calculating the pressure coefficient of NACA 4412. The results prove its credibility and value further more.