Abstract: The proposed device comprises a system of vertical and horizontal ropes fastened to an aircraft model at points located ahead and behind the model's center of gravity and secured in a wind tunnel through elastic members, which provides six degrees of freedom for the model in the throat of the wind tunnel. The system also includes a tensioning means for the horizontal ropes. The use of hoisting mechanisms connected to the elastic members of the vertical ropes makes it possible to adjust the position of the model in the throat of the wind tunnel both prior to and during experiments and thus dispense with controls to be mounted on the model. The proposed device makes it possible to simulate flight conditions for a wide variety of models within the subsonic speed range and fully eliminates what is known as suspension flutter. The invention is intended for experimental investigation of the dynamic strength and flutter characteristics of aircraft.