The invention discloses a method for recovering tail spin by controlling fore-body vortex and a flow control exciter. Different from a conventional method for recovering tail spin by providing reverse direct force via thrust vector and anti-spin parachute, the flow control exciter controls an aircraft forebody asymmetric flow and provides aerodynamic torque opposite to tail spin direction so as to recover the tail spin. The flow control exciter used by the method is an improved zero-net-mass-flux jet exciter and comprises a gyroscope, a microprocessor, a head apex, an air guide tube, two cavities and a vibration exciter; the flow control exciter is embedded in an craft head apex; the flow control exciter is low in energy consumption and quick in response during controlling the tail spin, and is applicable to engineering application. The method comprises the following specific processes: analyzing output signals of the gyroscope to obtain the tail spin direction and rotation speed when the aircraft enters the tail spin, then sending commands to the flow control exciter, controlling the aircraft for-body asymmetric vortex to form a right vortex type or a left vortex type; controlling the aircraft to reduce the rotation speed and reduce the incidence angle to recover the tail spin as the generated aerodynamic torque is opposite to the rotation direction of the aircraft.