空气动力学学报2017，Vol.35Issue(6)：792-796,5.DOI:10.7638/kqdlxxb-2015.0068
过失速薄翼增升流动控制方法
Lift enhancement control method of thin flat-plate at post stall angles of attack
吴继飞 1王志金 2GURSULIsmet3
作者信息
- 1. 空气动力学国家重点实验室,四川 绵阳 621000
- 2. 中国空气动力研究与发展中心,四川 绵阳 621000
- 3. 巴斯大学 机械工程系 航空航天工程研究中心,巴斯 BA27AY,英国
- 折叠
摘要
Abstract
An investigation on lift characteristics of thin flat-plate airfoil was conducted in a low speed wind tunnel.The effect of suction on the airfoil surface was studied in this experiment at various locations downstream of the airfoil leading-edge with different suction coefficients.A strain gauge force balance was used to measure the axial force and normal force on the airfoil.A TSI 2D-PIV system was used to measure the velocity field over the airfoil.The free stream velocity is 5 m/s,and the Reynolds number is 6.7×104/m.The results indicate that appropriate suction flow control has the effects of delaying the stall angle of attack by 7°and nearly double enhancing the lift coefficient.When suction is applied near the leading-edge,it may be easier to reattach the flow for smaller suction coefficients.However,for the suction coefficients in a certain range,the lift of the airfoil almost keeps constant with increasing suction coefficient. There is an optimal location for the suction control.A maximum lift coefficient can be generated for suction coefficients less than 3% when x/c equals to 0.4.关键词
薄翼/流动控制/吸气/失速/增升Key words
thin flat-plate/flow control/suction/stall/lift enhancement分类
航空航天引用本文复制引用
吴继飞,王志金,GURSULIsmet..过失速薄翼增升流动控制方法[J].空气动力学学报,2017,35(6):792-796,5.
