翼型边界层分离对动态失速模型的影响研究

The Effect Research of Airfoil Boundary Layer Separation on Dynamic Stall Model

Leishman-Beddoes模型因具有明确的物理概念和较高的计算精度而被广泛地应用于风力机设计和分析中。然而由于该模型来源于直升机旋翼翼型,直接应用于风电机组风轮翼型时存在较大的偏差。为此,针对典型风力机翼型开展了边界层分离响应规律研究,在此基础上通过对S809翼型定常气动载荷分析,提出了新的边界层分离点响应计算公式。通过对比分析不同状态下的动态失速特性得出,新的边界层分离响应公式能够有效改善风力机翼型边界层分离迟滞的计算精度,从而提高了动态失速模型的非定常气动载荷计算准确性。

The Leishman-Beddoes model is wildly used in wind turbine design and analyze because it has specific physical conception and better computational accuracy.However,there is a large deviation when it is directly applied to wind turbine airfoil,which derived from helicopter rotor airfoil.Therefore,the boundary layer separation response law of typical wind airfoil is studied in this paper.Based on this,a new boundary layer separation response formula is proposed by analyzing the steady aerodynamic load of S809 airfoil.Through comparative analysis of dynamic stall characteristic under different states,the new proposed boundary layer separation response formula can effectively improve the calculation accuracy of boundary layer separation hysteresis of wind turbine airfoil.Therefore it improves the accuracy of unsteady aerodynamic load calculation of dynamic stall model.