关键词: 鼓包, 不同截面, 非对称涡, 侧力, 航向控制

Abstract:

When a fighter aircraft or missile flies at high angle of attack(AOA),asymmetric vortexes are produced from the forebody and induce strong side force and yawing moment. In order to reduce the side force and yawing moment by controling the asymmetric vortexes, the effects of bumps on the forebodies are investigated. Tests with force measurement in a wind tunnel and with flow visualization in a water tunnel are performed.

Key words: bump,  , different , sections,  , asymmetric , vortex,  , side , force,  , yaw , control