摘要
为研究前缘对翼型气动性能影响,以NACA0012翼型为基础,通过曲线参数化方法改变翼型前缘吸力面及压力面型线,设计了8种不同前缘的翼型,并采用SST k-ω湍流模型研究了翼型在俯仰运动过程中的动态失速特性。结果表明:翼型动态失速特性受翼型压力面外形的影响较小;翼型吸力面加厚,将有效改善俯仰运动过程中的动态气动性能;翼型前缘弯度上弯将加剧翼型失速现象;翼型前缘弯度下弯可在一定程度上有效抑制动态失速现象,且变形量越大,抑制效果越好。
In order to study the effect of deformed airfoil leading edge on its aerodynamic performances,airfoils based on NACA0012 with 8 different deformed leading edges are designed by applying curve parameterization method and changing airfoil geometry.SST k-ωturbulent model is utilized to study the dynamic stall characteristics.The results show that lower surface geometry has small effects on the performance.Thicker upper surface could improve performance when pitching.Upward bended leading edge could escalate stall,while downward bended leading edge could suppress dynamic stall,and stronger bending leads to better suppression.
作者
邹锦华
李春
卜庆东
郝文星
ZOU Jin-hua;LI Chun;BU Qing-dong;HAO Wen-xing(School of Energy and Power Engineering,University of Shanghai for Science and Technology,Shanghai,China,Post Code:200093)
出处
《热能动力工程》
CAS
CSCD
北大核心
2019年第9期57-66,共10页
Journal of Engineering for Thermal Energy and Power
基金
国家自然科学基金(51176131)~~
关键词
翼型参数化
前缘修改
俯仰运动
动态失速
airfoil parameterized
leading edges modified
pitch motion
dynamic stall
