高亚音速下翼型非定常气动力数值仿真研究  

Numerical Simulation of Unsteady Aerodynamic Loads at High Subsonic Mach Numbers

作　　者：钱宇[1] 邓月莲 肖艳平[1] 

机构地区：[1]中国民航飞行学院飞行技术学院,四川广汉618307 [2]中国东方航空股份有限公司运行管理部,上海200051

出　　处：《计算机仿真》2013年第1期165-168,共4页Computer Simulation

摘　　要：非定常气动力的研究是气动弹性研究的基础。针对高亚音速下翼型强迫周期运动的非定常气动力数值模拟,采用Jameson提出的有限体积法求解Euler方程,利用具有二阶离散精度的双时间隐式推进方法,在验证了程序可靠性的基础上,研究了高亚音速时不同飞行马赫数、初始迎角、振幅和减缩频率时翼型做强迫俯仰振荡的迟滞效应。仿真结果表明,随着飞行马赫数的增加,迟滞环的面积逐渐增大,俯仰力矩系数的迟滞环随着马赫数走向将发生变化;俯仰力矩系数的迟滞环随着初始迎角的增大由动稳定变化为动不稳定,同时走向发生改变;随着减缩平率的增大,非定常迟滞效应越明显。The unsteady aerodynamic loads are the basis of the aeroelasticity. This paper focused on the computa- tion of the unsteady aerodynamic loads for forced periodic motions under high subsonic Mach numbers. The flow was modeled using the Euler equations and an unsteady time-domain solver was used for the computation of aerodynamic loads for forced periodic motions. The Euler equations were discretized on curvilinear multi-block body conforming girds using a cell-centred finite volume method. The implicit dual-time method proposed by Jameson was used for time-accurate calculations. Rigid body motions were treated by moving the mesh rigidly in response to the applied si- nusoidal motion. For NACA 0012 airfoil, a validation of the unsteady aerodynamics loads was first considered. Fur- thermore, a study for understanding the influence of motion parameters, the Mach number, the mean angle of inci- dence, the reduced frequency, the amplitude, was also conducted. A reverse of the trend of hysteretic loops can be observed with the increasing of the Mach number. Nonlinear hysteretic loops were turned up when increasing the am- plitude and the reduced frequency during the applied pitch sinusoidal motion.

关 键 词：数值模拟 非定常流动 迟滞效应 迟滞环 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]