摘要
用CFD方法对VR-12翼型可压缩动态失速的变下垂前缘控制概念进行了数值模拟研究.模拟结果显示,变下垂前缘控制能在最大升力下降不大的情况下,非常显著地降低最大阻力,减小俯仰力矩负峰值,明显改善动态失速的负面效应.在流动机理上,变下垂前缘控制完全消除了动态失速涡.对参数影响的模拟研究表明,变下垂前缘控制的优势对马赫数、简缩频率或下垂控制方式的变化不敏感,是一种健壮的翼型可压缩动态失速控制手段.
Numerical simulation for the variable droop leading-edge （VDLE） concept proposed to control the compressible dynamic stall of the VR-12 airfoil was presented. Computational results validate that VDLE can decrease considerably the maximum drag and improve the minimum pitching moment simultaneously while the lift is maintained almost at the same high level. The reason for VDLE having achieved these benefits, from the perspective of flow mechanism, is its ability to eliminate completely the dynamic stall vortex occurred on the baseline. Investigation of the effects of parameters shows that the control benefits of VDLE are not sensitive to the variation of Mach number, reduced frequency or drooping control methods, which implies that the VDLE is a robust control method for the compressible dynamic stall of airfoil.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2008年第3期496-504,共9页
Journal of Aerospace Power
基金
西北工业大学翼型
叶栅空气动力学实验室基金(51462010305KG2901)
关键词
航空
航天推进系统
翼型
动态失速
流动控制
数值模拟
aerospace propulsion system
airfoil
dynamic stall
flow control
numerical simulation
