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In this work, the Hydra Technologies Unmanned Aerial System (UAS) wing was simulated in several flight conditions. The simulations were carried out with the FLUENT Computational Fluid Dynamics code in 2D, and the grid was drawn with ICEM. Simulations were conducted using the turbulent models Spalart-Allmaras, SST k-ω and transition SST k-ω. The calculated results were compared with Xfoil. This comparative study allowed increasing the accuracy of the results as for the aerodynamic parameters of the wing CL, CD, CM and CP. The parallel objective was to determine the transition point. All the turbulent models were able to accurately simulate the correct behavior of the CP but transition SST k-ω appeared to be the only one able to find the transition point. In this study, we simulate, in 2D, a specific section of the wing located at the wing tip.