In this work, a 6-degree of freedom high AOA model was developed and identified using flight data from spin tests. Each wing panel was modeled separately according to Kirchhoff’s theory of flow separation. Due to rotation rates, each wing experiences different local AOA, which causes asymmetries on lift and drag. These effects contribute for roll and yaw moments, respectively. Additional aerodynamic terms due to the fuselage, as well as the horizontal and vertical tails, are added in order to model the overall aircraft force and moment coefficients during all spin phases: spin entry, developed spin and recovery. Using a model with more physical insight and less parameters than most high AOA models would usually require, it was possible to achieve good agreement with flight test data.