A STUDY OF DIFFERENT MESH GENERATION APPROACHES TO CAPTURE AERODYNAMIC COEFFICIENTS FOR HIGH-LIFT CONFIGURATIONS

摘要

The paper presents three-dimensional simulationsover a trapezoidal wing with a single slottedflap and a slat, which was a model developedin order to provide a database for CFD validation.This semi-span model has been tested bothin the NASA Ames 12-Foot Pressurized Tunnel(PWT) and the NASA Langley 14 by 22 FootSubsonic Wind Tunnel (SWT). The simulationsare performed for two flaps deflections, 20 and 25degrees, and a few angles of attack; the slat deflectionis hold constant at 30 degrees. Differentmesh methodologies such as hexahedral meshes,and hybrid prismatic-tetrahedral meshes are usedto perform the numerical simulations. In orderto observe the accuracy of the obtained aerodynamiccoefficients, with respect to mesh refinement,a small number of simulations is performedwith finner meshes. The baseline grids rangefrom 7.2 million to 12.8 million cells, while thefinner grids are around 23 million cells.