Rear Wing (~Formula One Dimensions)

grabcad

The article "Numerical Investigation of the Effect of Leading-Edge Tubercles on Propeller Performance" can be found here, while this publication is available as well. For inquiries, feel free to DM. The CFD analysis was conducted on a 250 mm span rear wing with modified leading edge, using meshes with approximately 300,000 cells. A range of tubercle amplitudes and wavelengths were tested, with larger amplitudes and smaller wavelengths proving more aerodynamically efficient. The selected configuration yielded a 15.28% increase in downforce and a 15.61% increase in the downforce-to-drag ratio, while also being 20.57% lighter than the baseline model. A static linear FEA was performed using fluid pressure and shear stress data from the CFD analysis, resulting in a FOS of approximately 16. The modified wing can be printed without issues after rotation around the z-axis. Similar principles apply to modified helical Darrieus wind turbine blades, rotor blades, and propellers, albeit in different application areas.