不同攻角和翼型的简化角冰特征参数的气动数值模拟  

Aerodynamic Numerical Simulation of Characteristic Parameters of Simplified Horn Ice at Different Angles of Attack and Airfoils

作　　者：郑诚毅 东乔天 赵宾宾[2] 金时彧 隋冬雨 杨志刚 李伟斌[5] 金哲岩[1] ZHENG Chengyi;DONG Qiaotian;ZHAO Binbin;JIN Shiyu;SUI Dongyu;YANG Zhigang;LI Weibin;JIN Zheyan(School of Aerospace Engineering and Applied Mechanics,Tongji University,Shanghai 200092,China;COMAC Shanghai Aircraft Design and Research Institute,Shanghai 201203,China;AECC Commercial Aircraft Engine Co.Ltd.,Shanghai 200241,China;Shanghai Automotive Wind Tunnel Center,Shanghai 201804,China;China Aerodynamics Research and Development Center,Mianyang 621000,Sichuan,China)

机构地区：[1]同济大学航空航天与力学学院,上海200092 [2]中国商用飞机上海飞机设计研究院,上海201203 [3]中国航发商用航空发动机有限责任公司,上海200241 [4]上海地面交通工具风洞中心,上海201804 [5]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《同济大学学报（自然科学版）》2021年第10期1443-1450,共8页Journal of Tongji University:Natural Science

基　　金：国家数值风洞工程项目(NNW2019ZT2-B26);结冰与防除冰重点实验室开放课题(AIADL20180102)。

摘　　要：选取常规翼型NACA23012、自然层流翼型NACA64-215和超临界翼型RAE2822,以冰角高度、冰角宽度,冰角端部形状以及冰角之间的连接情况4个参数来研究角冰对不同翼型在不同攻角下的升阻力系数的影响。结果表明,角冰的下冰角是影响翼型升阻力系数的主要原因之一,且不同翼型对参数的敏感性不同。同时,增加预测模型的升力性能可以通过选择半圆形的冰角端部形状、增加冰角之间的连接和减小冰角高度来实现。This paper selects the conventional airfoil NACA23012,natural laminar flow airfoil NACA64-215 and supercritical airfoil RAE2822,with four parameters including the height,width,end shape of horn-ice,and connection between horns,to study the influence of these four parameters on the lift/drag coefficient of different airfoils at different angles of attack.The results show that the lower horn of horn-ice is one of the main factors affecting the coefficient,and the sensitivity of different airfoils to parameters is different.The lifting performance of the prediction model can be increased by selecting the semicircle end,adding the connection between horns and decreasing the height of the horn-ice.

关 键 词：升阻力系数 角冰 常规翼型 自然层流翼型 超临界翼型 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]