Surrogate Modeling of Non-Linear Folding Wing Tip Aerodynamic Coefficients

The development of sustainable and efficient aircraft concepts, such as those featuring flared folding wing tips (FWTs), introduces both aerodynamic and structural challenges. FWTs have demonstrated strong potential for enhancing aerodynamic performance and alleviating gust-induced loads, making them an attractive option for next-generation transport aircraft. This study investigates the load reduction potential of transonic transport aircraft configurations equipped with hinged FWTs, with particular focus on gust impact. Reynolds Averaged Navier Stokes simulations are combined with Gaussian Process regression to evaluate the influence of the fold angle, flare angle, and angle of attack on key quantities of interest, including lift and wing root bending moment coefficients. The GP surrogate model, developed within the Gust Load Alleviation by Non-linear Folding Wing Tip (GUSTAFO) project, accurately reproduces the high-fidelity data while capturing the underlying system uncertainties. The results show that increasing the flare angle within a given folding deflection can reduce the wing root bending moment by up to 38% for flare angles between 0–45∘ and fold angles between 0–15∘. These findings highlight the effectiveness of surrogate-based modeling for early-stage design and emphasize the importance of incorporating FWT behavior to achieve accurate, efficient, and robust load predictions.     «

The development of sustainable and efficient aircraft concepts, such as those featuring flared folding wing tips (FWTs), introduces both aerodynamic and structural challenges. FWTs have demonstrated strong potential for enhancing aerodynamic performance and alleviating gust-induced loads, making them an attractive option for next-generation transport aircraft. This study investigates the load reduction potential of transonic transport aircraft configurations equipped with hinged FWTs, with parti...     »