The current study presents the investigation of the cant angle morphing winglet concept on a tactical, fixed-wing, Blended-Wing-Body (BWB) Unmanned Aerial Vehicle (UAV). The potential of the cant angle morphing winglet concept is assessed at various operating conditions, also including critical stability and trimming considerations. The objectives of this work are 1) to show the importance of including all key metrics (aerodynamics, performance, stability) into the evaluation process and 2) to propose an efficient methodology that allows this evaluation to be conducted. The cant angle is defined as the primary morphing winglet parameter and a total of 7 alternative configurations are generated. These configurations are investigated using high-fidelity, computational modeling (Computational Fluid Dynamics – CFD). The CFD results are in turn used to develop a surrogate model, so that the evaluation of the cant angle morphing winglet can be conducted throughout the entire cant angle range. The evaluation is conducted in three main steps, the first of which is a calculation of the changes in aerodynamic efficiency and corresponding net performance results. In the second step, some key stability-related constraints are also introduced and, at the third step, the effect of trimming is applied. The results for each of the three steps are presented in detail and are accompanied by a dedicated comparison section. An important conclusion of this work is that the stability aspects can by no means be ignored, since they drastically affect the cant angle morphing aerodynamic efficiency and performance enhancement potential.