摘要
基于运动嵌套网格方法建立了一套针对直升机旋翼/机身/平尾非定常干扰流场的数值模拟方法,并通过ROBIN机身和Caradonna&Tung旋翼算例进行了验证。应用该方法计算了悬停和前飞状态下直-9直升机旋翼/机身/平尾干扰流场,并与孤立旋翼、孤立机身流场的数值模拟结果进行了对比,分析了不同前飞速度下的旋翼/机身/平尾非定常气动干扰规律。计算结果表明,机身对旋翼诱导速度的干扰具有很强的方向性,并且会导致旋翼桨尖涡涡管畸变,引起旋翼拉力系数波动峰峰值增加;在旋翼下洗流作用下,机身/平尾表面呈现出复杂的非定常压力分布;随前进比增大,旋翼尾流远离平尾区域,气动干扰显著减弱。
A numerical simulation method based on the moving-embedded grid method is developed to analyze the aerodynamic interaction between the rotor,fuselage,and horizontal tail.The validity of this method has been established by comparing the results with ROBIN fuselage and Caradonna&Tung rotor test cases.Subsequently,this method is applied to calculate the interaction flow field between the rotor,fuselage,and horizontal tail of the Z-9 helicopter during hover and forward flight.The results are then compared with numerical simulations conducted for isolated rotor and fuselage flow fields.The law of unsteady rotor/fuselage/horizontal tail interaction at various forward flight speeds is analyzed.The results indicate that the fuselage induces strong directional interference with the rotor induced velocity,leading to the tip vortex tube distortion and an increase in the peak-to-peak value of the rotor thrust coefficient.In the presence of rotor downwash,the fuselage and horizontal tail experience a complex and unsteady pressure distribution.As the advance ratio increases,the rotor wake moves away from the horizontal tail,resulting in a significant reduction in aerodynamic interaction.
作者
张天毅
徐国华
史勇杰
胡志远
ZHANG Tianyi;XU Guohua;SHI Yongjie;HU Zhiyuan(National Key Laboratory of Helicopter Aeromechanics,Nanjing University of Aeronautics&Astronautics,Nanjing 210016,China)
出处
《南京航空航天大学学报》
CAS
CSCD
北大核心
2024年第3期534-544,共11页
Journal of Nanjing University of Aeronautics & Astronautics
基金
江苏高校优势学科建设工程。
关键词
直升机
计算流体力学
干扰流场
运动嵌套网格
数值模拟
helicopter
computational fluid dynamics
aerodynamic interaction
moving-embedded grid
numerical simulation
