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采用计算流体力学(CFD)的方法对洁净NACA0015翼型和两种典型温度下所形成积冰翼型的气动特性进行数值模拟与分析。流动控制方程为不可压方程,采用湍流模型。数值计算所得洁净翼型升阻力系数与文献中的实验结果较为吻合,表明了方法的可行、有效性。通过对不同攻角下升阻力特性、6°攻角下压力分布特性和14°攻角下积冰翼型绕流流动特性的数值计算,分析了积冰对翼型气动特性的影响。
The aerodynamic characteristics of the clean NACA0015 airfoil and the ice-formed airfoils formed at two typical temperatures were numerically simulated and analyzed by Computational Fluid Dynamics (CFD). The flow control equation is an incompressible equation, using a turbulence model. Numerical calculation of the clean airfoil drag coefficient and the experimental results in the literature more in line, indicating that the method is feasible and effective. The effects of ice accretion on the aerodynamic characteristics of airfoils are analyzed by numerical calculation of the ascending resistance at different angle of attack, the pressure distribution at 6 ° angle of attack and the flow around the ice sheet airfoil at 14 ° angle of attack.