Abstract: Compared to traditional over-shoulder-launched aircrafts, aircrafts based on the post-stall re-orientation technique have operational advantages, such as short response time, high manoeuvrability, and long range. Therefore, it is an advantageous option for the new generation of air-launched aircrafts to achieve omnidirectional attack. Focusing on the manoeuvre course of the post-stall re-orientation slender body, CFD simulations were performed to analyze the aerodynamic characteristics in this study. By improving the differential equation method, the hysteresis characteristics that exist in the post-stall re-orientation process can be successfully predicted. At the same time, the applicability of the least square support vector machine(LS-SVM) method in modeling such a problem has been verified. The present method can capture the non-linear unsteady aerodynamic characteristics in the re-orientation process, which provides a foundation in the control law design for post-stall re-orientation slender body.