28 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES 1 Abstract A Computational Fluid Dynamics (CFD) analysis of the high Reynolds number (Re ｧ 94k) flow around a quasi-2D spinning cylinder in a crossflow, using a high resolution 3D time marching unsteady Navier-Stokes solver was conducted. The lift coefficients predicted were in fair agreement with experimental results except in the Inverse Magnus Effect region (0.4 < ȍ < 0.7). The fact that these simulations were computed as purely laminar boundary layer flows, and failed to resolve any evidence of the Inverse Magnus Effect, would tend to support the proposition that the Inverse Magnus Effect is associated with boundary layer transition. The trends in the experimentally measured shedding frequency with cylinder spinning speed were captured reasonably well by the numerical model which resolved the initial rise in vortex shedding frequency with increased ȍ, followed by a rapid fall. At ȍｧ 2, suppression in the vortex shedding was observed and this finding demonstrates that vortex shedding degradation and suppression with increase in velocity ratio is still present even for high Re flow in the subcritical regime. 1 Introduction An attempt to harness the energy generated from the ‘Magnus Effect’ from spinning cylinders was made by Anton Flettner [1] in the mid 1920’s. Later he demonstrated the concept by replacing the conventional sails by spinning circular cylinders for the propulsion of large ships, through the modification of the ‘Buckau’ and ‘Barbara’. However, being a function of the ambient wind speed the cylinder’s performance was vulnerable, and due to the large availability and low cost of fuel in that era the idea was rendered redundant. The UAV (unmanned aerial vehicle) or MAV (micro air vehicle) industry is currently expanding due to these crafts ability to operate in hostile and inhospitable environments. An elaborate feasibility study conducted by C. Badalamenti [2] during his Doctoral research has demonstrated that spinning cylinders can be an alternative for conventional fixed wings when high lift to drag ratio is required. In addition, unlike conventional wings spinning cylinders are not constrained by stall and therefore could therefore offer increased payload capability. Further benefits in mission performance might be achieved during operations in high density ambient conditions such as in Polar latitudes. One interesting application where high lifting capability would be essential, and which needs some investigation, would be for flight vehicles for the unmanned exploration of extra-terrestrial environments such as the surfaces of Mars or Titan. The lack of application for rotating cylinder wings due to practicality issues at high subcritical Reynolds number (Re) has hampered the research directed towards understanding the highly complex flow physics, especially within the viscous layer and the behaviour of the vortical wake. Experimental investigations at high Re are usually hindered by structural dynamics issues related to the model and there are still arguments on the vortex shedding mechanism at high velocity ratios. Therefore, a numerical study has been launched to investigate whether the vortex shedding and the A COMPUTATIONAL STUDY OF THE AERODYNAMICS OF A SPINNING CYLINDER IN A CROSSFLOW OF HIGH REYNOLDS NUMBER E. R. Gowree and S. A. Prince Centre of Aeronautics, City University London erwin.gowree.1@city.ac.uk; s.a.prince@city.ac.uk