尾缘厚度对风力机翼型气动性能的影响

摘要

利用CFD软件对DU00-W-212翼型进行数值计算,验证了SST k -ω湍流模型在CFD数值计算中的合理性.通过Profili中的修型功能,分别增大翼型尾缘的上下翼面厚度.分析了在雷诺数Re =3×106情况下,尾缘厚度对气动特性的影响趋势及机理.%To proving that the SST k - eis taked as the CFD numerical modeis of turbulence reasonably, using CFD software for DUOO - W -212 airfoil. The thickness of the upper and lower surface of trailing edge is increased by Profili. Effect of trailing edge thickness on aerodynamic performance and pneumatic analysis can be studied at Re =3 X 106.