南京理工大学学报（自然科学版）2026，Vol.50Issue(1)：31-39,9.DOI:10.14177/j.cnki.32-1397n.2026.50.01.004
边条翼布局导弹增升效果及动态特性研究
Lift augmentation and dynamic characteristics of missiles with strake wing configurations
摘要
Abstract
To investigate the effects of different strake wing areas on the lift characteristics and flight stability of missiles at high angles of attack,the root length of the strake wing was used as a deformation parameter for dynamic characteristics research.The aerodynamic derivatives of the international dynamic derivative standard model Finner missile are calculated using the forced oscillation method.The pitch combined dynamic derivatives calculation method was validated,and a comparative analysis was performed on the variations in lift-drag coefficient,center of pressure coefficient,and pitch combined dynamic derivatives of missiles with different strake wing areas at various Mach numbers.The results indicate that at high angles of attack,airflow separates at the leading edge of the strake,forming stable strake vortices,which significantly enhance the missile's lift coefficient in the subsonic region.As the strake wing area increases,both the lift coefficient and center of pressure coefficient increase,improving static stability.The trends in pitch combined dynamic derivatives for missiles with and without strakes are similar across different Mach numbers,with the absolute value of the derivatives peaking at Mach 2.0.At a constant Mach number,increasing strake area enhances missile stability when the root length ratio is below 1.6,but reduces stability when the root length ratio exceeds 1.6.关键词
边条翼/强迫振动/动态稳定性/大迎角Key words
strake wing/forced oscillation/dynamic stability/high angle of attack分类
航空航天引用本文复制引用
任凡,霍津锋,陶善聪,熊雪露,周毅..边条翼布局导弹增升效果及动态特性研究[J].南京理工大学学报（自然科学版）,2026,50(1):31-39,9.基金项目
国家自然科学基金(12472223 （）
52306249 （）
91952105) （）
中央高校基本科研业务费专项资金(30924010923) （30924010923）
