<p>The inflatable wing design executed in Unmanned Aerial Vehicles (UAVs) is an attempt to reduce weight and implement quick deployment. The undulated profile arising from the implementation of an inflatable wing design was analyzed in this work as a possible flow control method to improve the wing performance at flights prevailing in low-Reynolds number flows typical of UAVs. The phenomenon of flow separation delay resulting from the flow being tripped by the undulated profile was the subject of evaluation. Two-dimensional simulations were performed using the 4 equation Transition Shear Stress Transport (SST) and 2 equation K-Epsilon models to evaluate the effect of undulations on the stall and glide characteristics. Eppler 398 was used as the base profile. The simulations were carried out using ANSYS Fluent software package, which provides a robust platform for analyzing the aerodynamic performance of the wing profiles. Parametric analysis performed with varying undulation characteristics (radius and position) was used to gauge the undulations’ performance compared to that of the base profile.</p>