Experimental Evaluation of the ASWING Aeroelastic Framework: Aeroelasticity Model

This paper presents the experimental evaluation and subsequent modification of the aeroelastic capabilities of ASWING, a software developed at MIT. Experimental data from the literature are compiled to assess ASWING’s ability to accurately predict deflections and twists under steady flow conditions, as well as their impact on the effectiveness of aerodynamic control surfaces. Based on this analysis, modifications to the code are proposed to improve the prediction of flap and aileron rolling performance. The paper then explores predictions related to torsional and flutter divergence, highlighting the influence of various parameters, such as angle of attack and nacelle position. Limit-cycle oscillations are also examined. Further discussions address tailerons and transonic flutter. A subsequent section focuses on flared folding wingtips, evaluating their effects on gust alleviation, rolling performance, and flutter onset, along with ASWING’s capacity to model these phenomena. ASWING proves to be a well-suited predesign analysis tool for conceptual aircraft architectures, including boxed, joined, and strut-braced wings with or without flared folding wingtips.