针对风力机翼型反设计问题,通过求解由涡量表达的面元流函数方程,直接得到面元节点速度;通过计算沿流线的伯努利方程获得面元的压力系数,进而求得升力系数和力矩系数。应用所述涡面元法以NACA2412 为初始翼型,以NACA4412 压力系数为目标值,获得满足目标压力系数的新翼型。根据新翼型对一小型风力机进行优化设计。计算表明基于涡面元法的翼型反设计有较高精度,较广适应性。通过凸函数表达翼型几何参数,能满足不同初始翼型的优化设计及风力机叶片的设计要求。
To solve the problems in the inverse design of airfoil for wind turbine blade, the stream function equations expressed by vorticity were solved and the velocities at the panel nodes were directly obtained. The other parameters such as pressure coefficient, lifting coefficient as well as torque coefficient can be calculated via the Bernoulli equation. A new airfoil was obtained by using vortex panel method, taking NACA2412 as the original geometrical shape and the pressure coefficients of NACA2412 airfoil as the target. Optimization design for a small wind turbine was conducted by incorporating the newly obtained airfoil. Numerical test showed that the inverse design based on vortex panel method had high accuracy and wide adaptation. By using bump function to represent the geometry of the airfoil, optimization designs can be achieved for different initial airfoil geometry and wind turbine blade.
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