Abstr:Flow Around Finite-Height Circular Cylinder: Difference between revisions

Revision as of 11:45, 10 January 2011

Contributed by: Guillermo Palau-Salvador, Wolfgang Rodi, — Universidad Politecnica de Valencia, Karlsruhe Institute of Technology

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 ==== Abstract ====
-A low Reynolds number (Re=10000) flow around a NACA0012 airfoil with a Mach
-number of Ma = 0.4 was chosen to test a new implementation in the CFD code.
-The flow is visualized with contours of velocity and pressure fields and the
-vortex street downstream of the airfoil is illustrated using the Q-criterion.
-Furthermore, the lift and drag coefficients are calculated.
-The simulation was performed with the Finite Differences solver HiPSTAR (High
-Performance Solver for Turbulence and Aeroacoustics Research), written mainly
-by Richard D. Sandberg in Southampton.