Abstract: The low speed wind tunnel test of a aeroservoelastic (ASE) aircraft model about roll/lateral direction was introduced, in order to validate the analysis method about aircraft ASE stability and stability margin. The test model, subsystem of test, the ways to carry out test, the test content and the test result were discussed. Some techniques, such as the model suspend system, similitude method about control law, hydraulic control system, computer control for test, and data manage were described in detail. The test result can be used in practical aircraft design, and many experiences were obtained. Meanwhile, it is showed that the current ASE analysis method was feasible, but should be modified in further research.