数值模拟积冰翼型及气动特性分析  

Numerical Simulation of Icing Airfoil and Analysis of Aerodynamic Characteristics

作　　者：郎需巍 刘星[1] 

机构地区：[1]南京航空航天大学民航学院,江苏南京210016

出　　处：《航空计算技术》2015年第5期82-85,共4页Aeronautical Computing Technique

摘　　要：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 CFD method is used to numerical simulation and analysis the aerodynamic characteristic sofclean NACA0015 airfoil and icing airfoils which are formed under two kinds of different typical temperature.Flow-controlled equationis incompressible Navier-Stokes equation with S-A turbulent models.Lift and drag coefficients of clean airfoil showing innumerical calculation agree withthe experimental results well from the literatures which indicates the method is feasible and effective.This paper analyzed the influence of icing airfoil aerodynamic characteristics by the numerical calculation of the lift and drag characteristics in different incidences,the pressure distribution characteristics under 6 degree attack angle and the flow fields around airfoil under 14 degree attack angle.

关 键 词：数值模拟 气动特性 升阻力特性 压力分布特性 积冰翼型 冰形 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]