摘要
以DU91-W2-250翼段为研究对象,基于带转捩的SST k-ω湍流模型,分析涡流发生器(Vortex generator,VG)高度对翼段动态失速的影响规律。从翼段在动态失速时的升阻力系数、边界层速度型的演变规律、分离涡拓扑结构以及VG流向涡的发展等角度,研究h=5、6、7.5、10 mm四种高度的VG对风力机翼段的流动控制效果。研究发现,当VG高度增大,其增升效果明显,最大阻力增加,下俯阶段降阻程度加大。较光滑翼段而言,加VG翼段边界层的流体动能更大,边界层厚度更小。高度越大的VG,流向涡环量越大且受攻角影响程度变小,涡核高度增加,耗散程度越小。总体而言,h=7.5 mm的VG在下俯阶段增升降阻作用最明显,边界层流体动能增加程度最大,其流向涡弦向控制范围更广、耗散程度更小,可有效抑制流动分离。
Based on transition SST k-ωturbulence model,the DU91-W2-250 airfoil is used to study the effect of the height of vortex generator(VG)on the dynamic stall.The flow control effects of VG with four heights of h=5,6,7.5 and 10 mm are discussed in terms of lift-drag coefficient,velocity profile,stream-wise vortex and vortex field.The findings indicate that an increase in VG height significantly improves lift,maximizes the increase in drag,and enhances drag reduction during the down pitch phase.Compared to a smooth airfoil section,the airfoil section with VG exhibits greater kinetic energy in the boundary layer and smaller boundary layer thickness.The higher the height of VG generate increased streamwise vortex strength and are less affected by the angle of attack,with higher vortex core altitude and less dissipation.Overall,It is found that the VG with h=7.5 mm has the most significant effect on lift-increasing and resistance reduction in the down pitch phase,and increases the boundary layer fluid kinetic energy to a greater extent,and its stream-wise vortex chordal control is wider and less dissipative,which can effectively suppress the flow separation.
作者
冯俊鑫
赵振宙
陈明
江瑞芳
王丁丁
刘一格
FENG Junxin;ZHAO Zhenzhou;CHEN Ming;JIANG Ruifang;WANG Dingding;LIU Yige(College of Energy and Electrical Engineering,Hohai University,Nanjing 211100;China Resources Power Techonology Reseroh Institute Co.,Ltd.,Dongguan 518000;Institute of Ocean and Offshore Engineering,Hohai University,Nantong 226019)
出处
《机械工程学报》
EI
CAS
CSCD
北大核心
2024年第8期291-298,共8页
Journal of Mechanical Engineering
基金
国家自然科学基金(51876054,11502070)
南通市民生科技重点(MS22019018)资助项目。
