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利用经验公式、小攻角下翼型气动特性数据建立了翼型在-180°～180°攻角范围内的气动特性估算模型。以NACA0012翼型、NACA0015翼型为例,对翼型全流向范围的升力系数、阻力系数、力矩系数进行了估算,并对风力机翼型DU96-W-180的升力系数、阻力系数进行了估算,将估算结果与实验结果进行比较,验证了估算方法的合理性。
The aerodynamic characteristics of the airfoil in the range of -180 ° -180 ° angle of attack were established by using empirical formula and airfoil aerodynamic characteristics at small angles of attack. Taking NACA0012 airfoil and NACA0015 airfoil as examples, the lift coefficient, drag coefficient and moment coefficient of airfoil in the full flow direction are estimated, and the lift coefficient and drag coefficient of airfoil DU96-W-180 are estimated The results of the estimation are compared with the experimental results to verify the rationality of the estimation method.