翼型舵面偏转非定常流动数值模拟  

Numerical Simulation of Rudder Reflection Unsteady Flow of an Airfoil

作　　者：贾忠湖[1] 董海波[2] 柳文林[1] 郑小洪[1] 

机构地区：[1]海军航空工程学院飞行器工程系,山东烟台264001 [2]大连理工大学航空航天学院,辽宁大连116024

出　　处：《航空计算技术》2014年第3期58-61,65,共5页Aeronautical Computing Technique

摘　　要：针对NACA0012翼型舵面偏转问题,数值模拟了不同参数对翼型气动特性的影响。基于非结构动网格技术,采用ALE有限体积描述下的二维可压缩非定常N-S方程,计算通量采用Vanleer格式、时空二阶格式,利用Venkatakrishnan限制器抑制数值振荡。非定常计算结果表明,NACA0012翼型绕1/4弦点作周期性俯仰振动的升力系数和俯仰力矩系数结果与实验数据吻合良好,验证了数值方法的准确性;在翼型舵面表面有分离区产生,升力系数和俯仰力矩系数形成滞回环,在亚声速情况下,滞回环幅值较小,进入超声速阶段以后,幅值增大,随着翼型间缝隙宽度逐渐增加,翼型升力系数和俯仰力矩系数与无缝翼型相比逐渐降低。According to the rudder reflection problem of NACA 0012 airfoil,the influences of different parameters to aerodynamic characteristics are studied by numerical simulation .Based on dynamic unstructured grids,the 2D compression unsteady N-S equation with the ALE finite volume method is applied . The flux is calculated by Vanleer scheme and time-space 2D scheme.The Venkatakrishnan limiter is used to control numerical oscillations .The results show： The lift coefficient and pitching moment coefficient of NACA0012 airfoil periodicity pitching vibration winding quarter string point agree well with experimental .The veracity of numerical simulation is proved .The separation zone appears on the surface of airfoil rudder .The lift coefficient and the pitching moment coefficient come into being hysteretic loop .The hysteretic loop amplitude is small under subsonic velocity , and the hysteretic loop amplitude is bigger under supersonic velocity than that under subsonic velocity .The lift coefficient and the pitching moment coefficient fall along with the gap on the streamline patterns of airfoil adding .

关 键 词：NACA0012翼型 非定常流动 舵面偏转 有限体积法 数值模拟 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]