大攻角细长旋成体非对称涡组合扰动控制的数值研究  

Numerical study of combined perturbation control of asymmetric vortices on a slender body of revolution at high angle of attack

作　　者：冯峰[1] 柳阳[1] 孙德军[1] 

机构地区：[1]中国科学技术大学近代力学系,安徽合肥230027

出　　处：《空气动力学学报》2010年第4期365-371,共7页Acta Aerodynamica Sinica

基　　金：国家自然科学基金重点项目(10432020);高等学校学科创新引智计划(B07033)

摘　　要：使用数值模拟的方法,研究了采用三角扰动块加单孔位微吹气进行大攻角细长旋成体绕流非对称涡控制的组合扰动技术。结果表明,组合扰动可以实现旋成体侧向力的渐变控制。对流场结构的分析发现,组合扰动是通过改变旋成体头部流场涡结构从而实现了对整个非对称流场的控制,据此可以确定能实现侧向力控制的有效吹气孔周向位置。计算中还发现,吹气孔位于离顶部较远位置时,侧向力随吹气强度变化平缓易控制,但需以较大吹气强度为代价。A flow control technique,which combined a small geometrical perturbation and a microblowing near the tip,for the asymmetric vortices of flow around a slender body of revolution at high angle-of-attack is investigated numerically.The results demonstrate the ability of this technique to control the side force of the slender body of revolution.On basis of the vortices structure observation,it is found that the effectiveness of side-force control owes to the ability of microblowing to alter the vortices configuration near the tip of the slender body.The efficient blowing port circumferential angle can be determined hereby.The results also suggest that,when the blowing port is located further downstream of the nose,the side-force change more continuously,but with larger input power.

关 键 词：流动控制 大攻角 非对称涡 双稳态 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]