Experimental Study of Effects of Tail Wings on Submunition Aerodynamic Characteristics  

作　　者：王海福 李向荣 

机构地区：[1]State Key Laboratory for the Prevention and Control of Explosion Disasters,Beijing Institute of Technology, Beijing100081, China

出　　处：《Journal of Beijing Institute of Technology》2004年第3期331-335,共5页北京理工大学学报（英文版）

摘　　要：Aimed at the needs of deceleration of submunitions dispensed from the ballistic missile, wind tunnel tests were performed on the submunitions with different tail wing sizes at the Mach number range from 0.7 to 3.0 and the angle of attack range from 0° to 14°. Experimental data about the variance of aerodynamic coefficients with the Mach number and angle of attack were obtained systemically. The effects of the tail wing sizes on the drag coefficients and the center of pressure coefficients were discussed. Analyzed results show the arc tail wings designed are beneficial to both the deceleration effect and static stability. These results are significant to the tail wing design and its applications to the submunitions deceleration..Aimed at the needs of deceleration of submunitions dispensed from the ballistic missile, wind tunnel tests were performed on the submunitions with different tail wing sizes at the Mach number range from 0.7 to 3.0 and the angle of attack range from 0° to 14°. Experimental data about the variance of aerodynamic coefficients with the Mach number and angle of attack were obtained systemically. The effects of the tail wing sizes on the drag coefficients and the center of pressure coefficients were discussed. Analyzed results show the arc tail wings designed are beneficial to both the deceleration effect and static stability. These results are significant to the tail wing design and its applications to the submunitions deceleration..

关 键 词：wind tunnel tests aerodynamic characteristics DECELERATION static stability 

分 类 号：TJ413.9[兵器科学与技术—火炮、自动武器与弹药工程]