论文部分内容阅读
通过耦合求解二维定常RANS方程和基于线性稳定性分析的转捩预测程序,计算了DU97-Flat翼型的气动性能并与实验结果进行比较,结果表明该文方法可进行有钝尾缘厚度翼型的气动性能计算。使用耦合求解方法,以DU97-W-300翼型为例,计算几种常见的风力机翼型钝尾缘修型方法(直接截断、对称加厚、不对称加厚和翼面旋转等)得到的钝尾缘翼型的气动性能,并分析各种修型方法对气动性能的影响。结果表明:直接截断修型方法并未增加此翼型的升力系数但对阻力增加的影响最小;不对称增加厚度引起的升力系数增加最明显,但会引起翼型使用角度区域的移动;通过指数因子形式对称增加时,指数因子在1.8～2.5之间较适中。
The aerodynamic performance of the DU97-Flat airfoil was calculated and compared with the experimental results by coupling two-dimensional steady-state RANS equation and the transition forecasting program based on the linear stability analysis. The results show that the proposed method can be used with a blunt tail thickness wing Type of aerodynamic performance calculation. Using the coupled solution method, taking the DU97-W-300 airfoil as an example, several common methods for calculating the aerodynamic airfoil blunt trailing edge (direct truncation, symmetrical thickening, asymmetric thickening and airfoil rotation) are obtained The aerodynamic performance of the blunt trailing edge airfoil and the influence of various repair methods on the aerodynamic performance are analyzed. The results show that the method of direct truncation does not increase the lift coefficient of this airfoil but has the least effect on the increase of resistance. The increase of the lift coefficient caused by the asymmetric increase of thickness is the most obvious, but it will cause the airfoil to move in the angle region. As the factorial form increases symmetrically, the exponential factor is more moderate between 1.8 and 2.5.