空气动力学学报2025，Vol.43Issue(9)：39-50,12.DOI:10.7638/kqdlxxb-2024.0146
基于合成双射流的边条翼大迎角前缘涡控制研究
Numerical study of leading-edge vortex control of a strake-wing at large angles of attack based on dual synthetic jets
邓熠 1王浩 1赵志杰 1邓雄 1罗振兵 1刘源园1
作者信息
- 1. 国防科技大学空天科学学院,长沙 410073
- 折叠
摘要
Abstract
Strake wings at large angles of attack experience significant degradation in aerodynamic performance due to the leading-edge vortex breakdown phenomenon,the effective control of which,however,has yet to be thoroughly explored.This study proposes an innovative control method utilizing dual synthetic jets to delay the leading-edge vortex breakdown.The results indicate that the aerodynamic performance of a 76°/40° strake wing can be improved by installing dual synthetic jet actuators away from the sweep path of the leading-edge vortex.The proposed control method can delay the strake vortex breakdown and thereby increase the lift coefficient at a wide range of the angle of attack(α).For instance,the vortex breakdown was delayed by 8.4%of the chord length at α=40°;the lift coefficient was increased by 7.51%at α=35°.The reason for such a significant improvement in aerodynamic performance was the effective energy injection,achieved by an anti-phase operating manner of two jets that continuously pushed low-energy fluids to rotate in the same direction.This operation method enhanced the leading-edge vortex's capability to withstand the adverse pressure gradient,lengthened the chordwise extent of high-speed flows,and expanded the area of the low-pressure zone on the leeward side,thereby increasing the vortex lifting force.The above results demonstrate the dual synthetic jets's potential in the attitude control of slender wings.关键词
边条翼/合成双射流/前缘涡/涡破裂/涡升力/数值模拟Key words
strake-wing/dual synthetic jets/leading-edge vortex/vortex breakdown/vortex lift/numerical simulation引用本文复制引用
邓熠,王浩,赵志杰,邓雄,罗振兵,刘源园..基于合成双射流的边条翼大迎角前缘涡控制研究[J].空气动力学学报,2025,43(9):39-50,12.
