摘要
用低速风洞测力试验和襟翼处绕流的PIV测量试验研究锯齿形格尼襟翼在不同偏角下的增升效益 .结果表明 :锯齿形格尼襟翼能明显提高翼型的升力系数和大升力系数下的翼型升阻比 ,对于给定的襟翼弦长 ,存在一个最佳的襟翼偏角 ,在此偏角下 ,翼型升阻比不仅在大升力系数下有明显提高 ,而且在中小升力系数时升阻比也有一定的提高 .PIV测量表明从锯齿形格尼襟翼的齿边向上卷起的流向涡使上翼面后部气流向翼型表面吸附 。
Force and PIV local flow measurements were conducted in a low speed wind tunnel to study the effectiveness of serrated Gurney flap at different deflections. The results show that the serrated Gurney flap can significantly increase the lift coefficients and the lift-drag ratio of airfoil with high lift coefficients. For a given serrated Gurney flap, there is an optimum deflection at which the lift-drag ratio of airfoil can be increased not only at high lift coefficient but also at low and medium attack angles of attack. It was found that near-stream wise vortices shed from the serrated edges can make the flow attach to the upper surface near the trailing edge and delay flow separation.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2003年第3期202-204,共3页
Journal of Beijing University of Aeronautics and Astronautics
关键词
增升装置
后缘襟翼
气动特性
Aerodynamics
Aircraft
Airfoils
Wind tunnels
