Abstract
The effects of laminar boundary layer thickness and aspect ratio on the aerodynamics of a circular cylinder supported by two large end-walls were studied by measuring the surface pressures in detail. The relative boundary layer thickness δ/d was kept at 0.26 or 0.82, and the aspect ratio L/d was varied from 10 to 30. Consequentially, in the case of large δ/d, the base pressure coefficient and the drag coefficient vary greatly over the large spanwise range from the cylinder end. Then, the drag coefficient variation is closely connected with the relative boundary layer thickness.
