This is a set of high order computational grids for the simulation of inviscid flow over a wing with an elliptic planform. The wing has a span of 10 meter, a root chord length of 1 meter and consequently an aspect ratio Ar = 40/Pi. The profile of the wing is a symmetric NACA-0012 profile, hence zero lift is obtained for zero degree angle of attack. These grids are meant to be used in combination with a higher order finite element method (e.g Discontinuous Galerkin) to test how well the numerical discretization is able to predict the induced drag. Due to the large aspect ratio of the wing, lifting line theory can be used to predict the induced drag coefficient, CD_i, as a function of the lift coefficient CL, i.e. CD_i = CL^2/(Pi Ar). For the given aspect ratio of this wing this results in CD_i = 0.025*CL^2.
The following grids are available in CGNS format, version 4.5
FullWingHexOnlyCoarse_P3.cgns: Cubic grid of the full wing that consists of 13,056 hexahedra (CGNS element type HEXA_64)
FullWingHexOnlyMedium_P3.cgns: Cubic grid of the full wing that consists of 104,448 hexahedra (CGNS element type HEXA_64)
FullWingHexOnlyCoarse_P4.cgns: Quartic grid of the full wing that consists of 13,056 hexahedra (CGNS element type HEXA_125)
FullWingHexOnlyMedium_P4.cgns: Quartic grid of the full wing that consists of 104,448 hexahedra (CGNS element type HEXA_125)
The following grids are available in CGNS format, version 3.31
HalfWingTetOnlyCoarse_P4.cgns: Quartic grid of half the wing that consists of 16,100 tetrahedra (CGNS element type TETRA_35)
HalfWingTetOnlyFine_P4.cgns: Quartic grid of half the wing that consists of 1,567,956 tetrahedra (CGNS element type TETRA_35)
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