风力机叶片内侧翼型综合改型对翼型气动性能影响

摘要

For airfoil inside of the wind turbine blade, the aerodynamic performance before and after modification was studied.The law of comprehensive improvement of airfoil was revealed in relative thickness, relative camber and trailing edge thickness of the inside of the blade.Through Profili and Matlab software, parametric processing airfoil relative thickness, relative camber and trailing edge thickness of the airfoil were parameterized.Profili and Fluent software were used to simulate.And the drag coefficient, lift-to-drag ratio and airfoil surface pressure and velocity distribution of the improved airfoil were compared with the original airfoil.The results show that the comprehensive improvement of airfoil can not be simply by changing relative thickness, relative camber and trailing edge thickness according to their respective best comprehensive improvement, and the comprehensive improvement of airfoil method need to be studied further.Under the premise of ensure the structural strength the blade inside, according to the relative camber increase about 1% chord length on the basis of the best and the thickness of the trailing edge reduce about 2% chord length on the basis of the best, the improved airfoil aerodynamic performance is better.Study conclusions can be used by the wind turbine blade airfoil design and retrofit for quantitative reference.%针对风力机叶片内侧翼型,研究其改型前后的气动性能,揭示在叶片内侧相对厚度、相对弯度、尾缘厚度综合改进翼型的规律.通过Profili和Matlab软件对翼型相对厚度、相对弯度和尾缘厚度参数化处理,用Profili和Fluent软件数值模拟,对比原始翼型和改进翼型升阻力系数、升阻比及翼型表面压强和速度分布.结果表明:综合改进翼型不能单纯将相对厚度、相对弯度、尾缘厚度按各自最佳综合改进,需进一步研究综合改进翼型方法;在叶片内侧保证结构强度的前提下,按相对弯度在最佳的基础上增大1%弦长左右,尾缘厚度在最佳的基础上减小2%弦长左右,改进后的翼型气动性能较好.研究结论可供风力机叶片翼型设计和改型量化参考.