摘要
为研究有限展长结冰对旋翼气动特性的影响机理,建立了基于运动嵌套网格方法和URANS方程的旋翼流场求解方法。通过前飞状态AH-1G旋翼非定常气动特性对比分析,验证了数值求解方法的有效性;获得了结冰展向位置和温度对旋翼复杂流动特征、桨叶非定常载荷变化特性的影响规律。结果表明:桨叶剖面前缘冰形能产生额外的升力补偿;在一定结冰温度范围内,桨叶剖面气动特性恶化程度随结冰温度的降低而增大;有限展长结冰加剧了前飞状态下前行侧桨尖激波效应和后行侧桨叶结冰区域的动态失速效应。
In order to study the influence mechanism of finite-span ice accretion on the aerodynamic characteristics of rotor,the rotor flow field simulation method is established based on the moving-embedded mesh method and URANS equation.The effectiveness of the numerical solution method is verified by comparing and analyzing the unsteady aerodynamic characteristics of the AH-1G rotor in forward flight.The influence laws of icing spanning position and icing temperature on the complex flow characteristics of rotor,and the unsteady aerodynamic load variation characteristics of blade are obtained.The results demonstrate that the ice shape on leading edge of the blade section creates additional lift compensation.The deterioration of aerodynamic characteristics of the blade section increases with the decrease of icing temperature in a certain range of icing temperature.The finitespan ice accretion aggravates the shock wave of blade tip on the forward side and the dynamic stall of blade icing area on the rear side in forward flight.
作者
高陈诚
张夏阳
招启军
周雨萌
GAO Chencheng;ZHANG Xiayang;ZHAO Qijun;ZHOU Yumeng(College of Aerospace Engineering,NUAA,Nanjing 210016,China)
出处
《飞行力学》
北大核心
2025年第4期14-20,26,共8页
Flight Dynamics
基金
国家自然科学基金资助(12102186)
国家重点实验室基金资助(61422202201)
中国科协青年人才托举工程资助项目(2022QNRC001)
江苏高校优势学科建设工程资助项目
2024年度科技智库青年人才计划(XMSB20240710072)。
关键词
旋翼桨叶
有限展长结冰
运动嵌套网格
非定常气动特性
rotor blades
finite-span ice accretion
moving-embedded mesh
unsteady aerodynamic characteristics
