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以长耳鸮翼型为仿生原型,采用逆向工程方法提取鸮翼翼型下表面特征点并利用B样条曲线进行拟合建立鸮翼仿生重构模型。通过数值求解耦合Langtry-Menter SST模型的雷诺时均Navier-Stokes方程,研究了仿生翼型的前缘弧线曲率、前缘厚度、前端倾角、翼型中部下表面曲率以及尾部厚度等参数对翼型升阻比的影响,获得了一种能有效抑制大攻角下流动分离发生的仿生翼型。正交试验结果表明:翼型前缘厚度对仿生翼型的升阻比影响最大,随着翼型前缘厚度的减少,翼型升阻比增加;翼型下表面中部曲率和翼型尾部厚度均存在最优值使仿生翼型升阻比最大。
The long-eared wing airfoil was taken as a bionic prototype, and the reverse engineering method was used to extract the lower airfoil wing feature points and fitted with B-spline curves to establish the bionic wing reconstructed model. The Navier-Stokes equations of the Langtry-Menter SST model are numerically solved by the Navier-Stokes equations. The curvature of the leading edge of the bionic airfoil, the thickness of the leading edge, the inclination of the tip, the curvature of the lower surface of the middle airfoil, Type lift-drag ratio, a bionic airfoil that can effectively suppress the flow separation at a high angle of attack was obtained. The results of orthogonal test show that the thickness of the leading edge of the airfoil has the most significant effect on the drag-drag ratio of the bionic airfoil. As the thickness of the leading edge of the airfoil decreases, the drag-drag ratio increases. The curvature of the lower surface of the airfoil and the tail thickness of the airfoil There are optimal values to make the ratio of bionic wing lift-drag maximum.