NACA 0012 Wing Assembly with Rotating Cylinder

Create two separate NACA 0012 wing models in SolidWorks using MMGS units. Both wings must have a 40 mm chord, 240 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 240 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 230 mm length. The cylinder runs along the wingspan, perpendicular to the airflow, and is centred spanwise, leaving 5 mm at each wingtip. 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. Do not include the continuous steel shaft or the 10 × 2 mm steel reinforcement strip. 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

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