Abstr:Flow Around Finite-Height Circular Cylinder: Difference between revisions
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== Flows Around Bodies == | |||
=== Underlying Flow Regime 2-10 === | |||
==== 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. | |||
{{ACContribs | |||
|authors=Paul Altenhoefer;Dominic von Terzi | |||
|organisation=Universität Karlsruhe; Institute of Thermal Turbomachines; [http://www.turbo-dns.de Research group Turbo-DNS] | |||
}} | |||
{{UFRHeader | |||
|area=2 | |||
|number=10 | |||
}} | |||
© copyright ERCOFTAC 2011 | |||
Revision as of 11:40, 10 January 2011
Flows Around Bodies
Underlying Flow Regime 2-10
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.
Contributed by: Paul Altenhoefer;Dominic von Terzi — Universität Karlsruhe; Institute of Thermal Turbomachines; Research group Turbo-DNS
© copyright ERCOFTAC 2011