Numerical Simulation of the Aircraft Wake Vortex Flowfield | Zendy

Nashat N. Ahmad | Zendy

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Numerical Simulation of the Aircraft Wake Vortex Flowfield

Author(s) -

Nashat N. Ahmad

Publication year - 2013

Publication title -

nasa sti repository (national aeronautics and space administration)

Language(s) - English

Resource type - Conference proceedings

DOI - 10.2514/6.2013-2552

Subject(s) - wake , wake turbulence , aerospace engineering , vortex , mechanics , computer simulation , kármán vortex street , physics , computational fluid dynamics , marine engineering , computer science , engineering , turbulence , reynolds number

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 and Spalart-Shur corrections for rotation and curvature effects. The simulation results were evaluated using the data from an experiment performed at National Aeronautics and Space Administration (NASA) Ames’ 32 in. x 48 in. low speed wind tunnel.

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