Abstract: Static force measurements of blended-wing-body aircraft at high angles of attack were carried out in the 1 m low speed wind tunnel of Nanjing University of Aeronautics and Astronautics. By fully mining and analyzing the experimental results, the approximate initial departure angle of attack and departure region of BWB aircraft are obtained by using multiple criteria, including the static stability derivative, the dynamic directional stability parameter, the lateral control departure parameter and the Weissman chart. Besides, the spin sensitive region of BWB aircraft is predicted. At the same time, the departure is simulated by the virtual flight test in wind tunnel. The results show that the lateral stability of BWB aircraft is poor, and the non-command roll motion may occur at a very small angle of attack, which is also the main reason for the divergence of the departure. And the departure characteristics obtained from the virtual flight test and these stability criteria are in good consistency, which verifies the reliability of the virtual flight test in departure characteristics research.