不同来流条件对机翼结冰及气动特性影响研究  

Influence of different inflow conditions on wing icing and aerodynamic characteristics

作　　者：李庆庆 王军利[1] 李金洋 冯钰茹 陆正午 LI Qingqing;WANG Junli;LI Jinyang;FENG Yuru;LU Zhengwu(Mechanical Engineering College,Shaanxi University of Technology,Hanzhong 723000,China)

机构地区：[1]陕西理工大学机械工程学院,陕西汉中723000

出　　处：《飞行力学》2022年第3期13-20,共8页Flight Dynamics

基　　金：陕西省科学技术厅重点项目(2017ZDXM-GY-138);陕西省科学技术厅一般项目(2020JM-600);陕西省教育厅科研项目(19JK0172);陕西省工业自动化重点实验室开放课题(SLGPT2019KF01-13)。

摘　　要：针对三维机翼结冰问题,基于Navier-Stoke控制方程,采用多时间步长的计算方法,通过求解气液两相流的Eluer法得到空气中水滴的轨迹,再根据Messinger模型计算结冰冰形来实现对机翼结冰的数值模拟。首先以三维NACA0012机翼为研究对象,进行结冰数值模拟方法验证,随后计算不同迎角和不同来流速度对三维ONERA M6机翼结冰冰形的影响,最后分析了机翼结冰对气动特性的影响规律。结果表明,结冰后机翼的阻力系数增大,升阻比减小;来流速度对机翼前缘的结冰类型影响较大,当机翼前缘的结冰类型由霜冰变为混合冰时,将使机翼的气动特性恶化。Based on the Navier-Stoke control equation,a multi-time step method was adopted to calculate the trajectory of water droplets in the air by solving the gas-liquid two-phase flow Eluer method,and then the ice shape was calculated by Messinger model to realize the numerical simulation of wing icing.Firstly,a three-dimensional NACA0012 wing was taken as the research object to verify the icing numerical simulation method.Then,the effects of different angles of attack and inflow velocities on the icing shape of the three-dimensional ONERA M6 wing were calculated.Finally,the effects of wing icing on aerodynamic characteristics were analyzed.The results show that the drag coefficient increases and the lift-drag ratio decreases after icing.The flow velocity has a great influence on the icing type of the leading edge of the wing.When the icing type on the leading edge of the wing changes from frosty ice to mixed ice,the aerodynamic characteristics of the wing will be worsen.

关 键 词：机翼结冰 多时间步长 结冰冰形 气动特性 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程]