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利用SST k-ω湍流模型模拟光滑S809翼型风力机正弦振荡时动态气动特性,并同OSU(俄亥俄州立大学)风洞试验数据进行对比,表现出良好一致性,证明了所用方法有效性。对不同粗糙度S809翼型正弦俯仰振荡时动态气动特性进行数值模拟,得到了升力系数和阻力系数迟滞回环,分析得出该翼型动态气动特性临界粗糙度为0.4 mm。进一步对粗糙度为0.4 mm的粗糙带位于翼型压力面和吸力面不同位置时的动态气动特性进行模拟和分析,指出翼型动态气动特性对吸力面前缘10%位置粗糙带最为敏感,随粗糙带高度增加,翼型动态气动性能大幅降低,动态失速攻角提前。
The dynamic aerodynamic characteristics of a smooth S809 airfoil with sinusoidal oscillations were simulated by the SST k-ω turbulence model and compared with the wind tunnel test data of OSU (Ohio State University). The results showed good agreement and proved the effectiveness of the proposed method. The dynamic aerodynamic characteristics of S809 airfoil with different roughness are numerically simulated and the lift coefficient and drag coefficient hysteresis loop are obtained. The critical aerodynamic characteristics of this airfoil are obtained with a critical roughness of 0.4 mm. The dynamic aerodynamic characteristics of the rough belt with roughness of 0.4 mm at different positions of airfoil pressure and suction are simulated and analyzed. The dynamic aerodynamic characteristics of airfoils are the most sensitive to the 10% With a high degree of increase, aerodynamic performance significantly reduced airfoil, dynamic stall ahead of the attack angle.