Wing smarting and eliminating conventional control surfaces are fundamental parameters for improving aircraft aerodynamic performance in future aviation. A twist is a well-known tool that, along with the development of morphing technology, can play a crucial role in controlling next-generation aircraft. However, wing twisting with a control approach requires many aerodynamic studies, particularly at the high aft-swept angle; this is more noticeable in the flying-wing configuration. In this paper, a control strategy based on twist-morphing has been evaluated aerodynamically at the Swing, a flying-wing configuration. Extraction of aerodynamic coefficients and flowfields on the wing has been performed using the computational fluid dynamics (CFD) method in an incompressible flight regime. To comprehensively cover the control needs, two control concepts have been introduced called independent and non-independent twists. Within the concept of independent twist, co-oriented twist arrangement (Co-OTA) and counter-oriented twist arrangement (Cun-OTA) are applied to the wings, which are used to produce pitching and rolling moments, respectively. The results show these control arrangements have high efficiency at a low angle(s) of attack (AoAs), but as the AoA increases, their aerodynamic performance will gradually decrease. In this regard, a significant challenge for Cun-OTA is the production of the yawing moment during roll maneuvering. Attempts to solve this problem have led to the idea of a compound twist arrangement (CTA). The existence of a control arrangement to generate yawing moment is beyond the capacity of the independent twist concept. The non-independent twist has been introduced as a solution to this issue.

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