NACA 0012 Wing with Spanwise Rotating Cylinder (Exploded)

Create two separate NACA 0012 wing models in SolidWorks using MMGS units. Both wings must have a 40 mm chord, 200 mm span, and 4.8 mm maximum thickness. First, model the clean wing by importing accurate NACA 0012 airfoil coordinates and extruding the closed profile to 200 mm. Save a copy as the modified wing. On the modified wing, create an open-top cavity along the upper surface to accommodate a hollow rotating cylinder with a 5 mm outer diameter and 200 mm length. The cylinder runs along the wingspan, perpendicular to the airflow, and is centred spanwise. So yes, cylinder spans through the entire length of the airfoil. Position its centre at approximately 30% chord (x/c = 0.29983), around 12 mm from the leading edge, at the maximum-height region of the NACA 0012 upper surface. The cylinder is 60% embedded: 3 mm of its diameter lies below the original upper airfoil surface, while 2 mm protrudes above it. Maintain a provisional radial clearance of 0.65 mm between the cylinder and its cavity; the nominal clearance diameter is therefore 6.3 mm, but the final cavity must follow the open-top geometry. Include two 3 × 6 × 2 mm bearings and integrated bearing holders near the cylinder ends, ensuring proper alignment and free rotation. Design a suitable shaft-free connection between the cylinder and the bearing inner races, leaving the end-support details provisional until confirmed. Create a modified-wing assembly with appropriate mates that allow cylinder rotation and check for interference.

Parameters

Every value above is a live dimension. Open a model like this in the editor and each one becomes a slider you can drag before exporting.