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Numerical Simulation of the Aircraft Wake Vortex Flowfield
2013
5th AIAA Atmospheric and Space Environments Conference
unpublished
The near-wake vortex flowfield from a NACA0012 half-wing was simulated using a fully unstructured Navier-Stokes flow solver in three dimensions at a chord Reynolds number of 4.6 million and a Mach number of approximately 0.15. Several simulations were performed to examine the effects of boundary conditions, mesh resolution, and turbulence scheme on the formation of wingtip vortex and its downstream propagation. The standard Spalart-Allmaras turbulence model was compared with the Dacles-Mariani
doi:10.2514/6.2013-2552
fatcat:msdhxme3sjb65g6vwdlvm5qyv4