襟翼翼型位置对气动性能的影响研究  

Influence of the flap airfoils with different positions on the aerodynamic performance

作　　者：缪维跑 李春[1] 聂佳斌[1] 吴攀[1] 

机构地区：[1]上海理工大学能源与动力工程学院/上海市动力工程多相流动与传热重点实验室,上海200093

出　　处：《能源研究与信息》2015年第4期242-246,共5页Energy Research and Information

摘　　要：对NACA0012两段式襟翼翼型进行了数值模拟,通过弦线变换得到了襟翼摆角与攻角的关系,发现了襟翼翼型在静态条件下由摆角引起的攻角迁移现象,并解释了该现象的流动机理.计算了7种不同摆角襟翼在不同攻角下的气动性能,得到了襟翼摆角导致的翼型尾迹流场变化情况,并与实验值及Xfoil软件计算值对比以验证计算的准确性.结果表明,随襟翼摆角增大,有效攻角范围减小,翼型攻角产生迁移,受力亦发生变化.结果为进一步开展襟翼翼型的摆角控制策略研究提供了参考.The numerical simulation was conducted for two-segment flap airfoil of the NACA0012,which were trigged by the rotation of airfoil＇s flap.The relationship between the angles of the flap and the angles of attack（AOA）was obtained by the chord changing.The AOA shiftting caused by the oscillation of the flap under the static conditions was discovered.And the mechanism was revealed.Seven different angles of the flap were simulated with different AOAs to assess the aerodynamics performance.Then the wake vortex behavior was investigated.The comparison among the expariments,simulation,and Xfoil was made.It showed that the range of the effective AOA was narrowed and the AOA was shifted by raising the tilt angle.The pressure of the flap changed as well.The aforementioned results might give some control stratagies for the tilt angle of the flap.

关 键 词：数值模拟 襟翼 翼型 攻角 

分 类 号：TK83[动力工程及工程热物理—流体机械及工程]