This paper presents the concept of dynamic wind tunnel testing using captive flight method, in which the airplane is supported by three elastic lines mainly in the vertical direction, and given oscillatory motions by an external actuator. This experimental method is designed for the aerodynamic parameter estimation. All of the captive flight modes are second-order systems. Longitudinal and lateral dynamic tests are carried out sweeping driving frequency, and every mode except surging motion, of which damping is weak, was excited. This experiment method has the advantages of the experimental simplicity, quite small aerodynamic interference, stable flight and the capability of excitation of motion necessary for the estimation.