Autonomous aerial systems have a growing range of applications in various areas such as agriculture and logistics. Within this branch, stand out the fixed and rotary wing Unmanned Aerial Vehicles (UAVs), because they have particular advantage over multirotor vehicles for their versatility, autonomy and eficiency. These aircraft generally operate at low speeds, hence in Reynolds number ranges around 200,000 to 400,000. In this range the flow can still be kept laminar over the pressure recovery region in the wing upper surface of these vehicles. Thus, the presence of laminar separation bubbles caused by the unfavorable pressure gradient may occur. These bubbles cause loss of lift and drag. In that way, the transition from laminar to turbulent flow may occur closer to the leading edge due to pressure distribution. In this case, the viscous drag of the turbulent boundary layer induces a loss of vehicle performance. Thus, this work proposes the application of two methodologies for airfoil performance improvement typically used in medium range UAV projects. Firstly, it will be analyzed the application of distributed roughness, represented by the so-called Trips of the boundary layer, in specific points of the airfoil upper surface aiming to avoid the formation of laminar separation bubbles. Then the laminar-turbulent boundary layer transition delay technique will be analyzed using Laminar Flow Control (LFC), more specifically Natural Laminar Flow. This strategy involves altering the original geometry, seeking to extend the laminar boundary layer and reduce frictional drag. For this a numerical analysis software is used for airfoils under low Reynolds flow conditions. Results are compared using the drag polar metric. To quantify the gains, performance analysis will be executed.