The aim of this project is to carry out an aerodynamic performance analysis of a paraglider by using simulation computational programs with low time cost and computational requirements, but still effective approach obtaining reliable results. To achieve this objective, a 3D analysis of the wing will be done using PARACHUTES, a simulation program based on a flow potential theory approach, complemented with an unsteady low order panel method. To consider viscous phenomenon, boundary layer thickening effects and flow separation, a 2D analysis will be done using XFOIL simulation program. To perform this study, the CAD 3D model has to be parameterized and the boundary conditions has to be properly configured previously for the acquisition of accurate results. Moreover, to complement it with the 2D analysis, these geometries are obtained from the 3D CAD model and some parameterization has been also done. First, a study of the pressure coefficient and velocity distribution contours will be done. Then, a 2D comparison of two airfoils that conform the wing will be analyzed. Next, the common aerodynamic parameters will be determined and studied: lift coefficient (CL), drag coefficient (CD), pitching moment coefficient (CM). The equations that define the previous parameters are also determined. Finally, a comparison between the results obtained in this project with CFD simulation results provided by Niviuk Gliders is performed.