Investigation of Near-Field Flow Unsteadiness Around a NACA0012 Wingtip Using Large-Eddy-Simulation Approach
説明
Three-dimensional unsteady flow around NACA0012 wingtip is simulated numerically to investigate the cause of flap-edge noise generation. The vortical flow structures around the NACA0012 are known to be similar to that of a flap-edge. Therefore, it is assumed that noise generation mechanism is similar as well, although its geometry is simpler than a flap-edge. Since the Reynolds number of the flow is high, a zonal LES/RANS hybrid method is used to reduce the overall computational cost. The power spectral density of the pressure coefficient is compared with the experiment, and several issues regarding, the number of sub iteration for implicit time integration, sensitivity to Smagorinsky constant, grid overlap points at block-block interface, and grid resolution, are discussed. Subsequently, two longitudinal vortical structures around the wingtip, that show different characteristics, are investigated to understand its generation mechanism. The broadband nature of flow unsteadiness around the wingtip will be discussed.
収録刊行物
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- 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition
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48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition 2010-01-04
American Institute of Aeronautics and Astronautics (AIAA)