Abstract: With non-zero sideslip angle condition, the changing laws of side force and yawing moment of a slender body at high angles of attack were investigated through wind tunnel testing. An active flow control technique was used to control the slender body's side forces and yawing moments at non-zero sideslip angle, so as to study the controlling law and the range of effective controlling sideslip angles as well. The results showed that at the condition of α=55° and the range of sideslip angle β =-24°~+24°, the side forces and yawing moments showed linear changing laws at the effective azimuthally angle ranges (±16° ) through changing the equilibrium position of a fast swing micro tip-strake installed on the slender model. When the phantom yaw movement of high agility combat aircraft occurs, this active linear flow control technique could be a new possible flight controlling method for aircraft recovering and safety.