This verification example analyzes the fluid flow around a glider’s wing profile by determining the drag and lift coefficients as functions of the angle of attack, which are useful for constructing a drag polar graph. The analysis identifies the limit angle for sustaining laminar flow, with results supported by a detailed velocity field study. A provided 3D CAD STL model is integrated within RWIND 2 to perform the simulation, while a visual representation reinforces the geometric details and flow contours around the airfoil. ©