F12全机动态特性数值模拟  

Dynamic Derivative Simulation of F12 Aircraft Configuration

作　　者：张一帆[1] 李中武[1] 姚冰[1] 李立[1] 

机构地区：[1]中航工业西安航空计算技术研究所气动数值模拟航空科技重点实验室,陕西西安710068

出　　处：《航空计算技术》2015年第2期22-25,30,共5页Aeronautical Computing Technique

基　　金：国家863计划项目资助(2012AA01A304)

摘　　要：采用非定常正弦振荡和准定常旋转坐标系两种数值模拟方法,对F12全机模型三个攻角进行动态特性数值模拟,得到飞行器的纵向组合动导数和阻尼动导数,计算结果与试验数据对比具有良好的一致性,同时用无粘和粘性两种计算方程进行准定常旋转坐标系模拟,计算结果一致,表明两种数值模拟方法准确性高,计算速度快,可为设计提供快速可信的数据支持。Two numerical simulation methodologies of the unsteady forced pitch oscillation and the quasisteady rotating reference frame are used for simulating DLR- f12 model. The unsteady dynamic derivative and the damping derivative are obtained; the results are in agreement with the experiment data. Meanwhile Euler and Navies-Stokes quasi-steady results are compared,the viscous effects are not significant.The result shows that the two numerical simulation methods presented here can provide feasible stability characteristics as a guidance of the design process.

关 键 词：非定常正弦振荡 准定常旋转坐标系 组合动导数 阻尼动导数 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]