The pressure distribution around the ONERA M6 wing at a 3º angle of attack was calculated using a single block. The equations solved were those for inviscid compressible flow at a Mach number of 0.84. The results were compared to the inviscid calculations of Jameson (1998).
The computational domain employed a block with 189 x 40 x 50 grid points. The grid is an O-grid with the i-direction oriented along the surface of the wing and the k-direction along the wing span. The simulation type is simple CFD using both the WENO and the MUSCL scheme for spatial differencing and the Beam-Warming scheme used for time differencing. The problem was solved using a far field assumption at the wing tip. Slip boundary conditions was applied at both the wing surfaces and the wing body surface at k = 1.
Both mesh files and project input files can be accessed below. Remember to place the grid files in a subfolder with respect to the set up file /farfield.
Change the directory to the subfolder with the set up file. Start the simulation by
mpirun –np 1 mpiaeroflo.exe < onera_sb.afl
Results for the coefficient of pressure were extracted along the span at points z/B = 12.5%, 31.25%, 50%, and 68.75%. The results are shown in Figure P7.1.
The results extracted at the above points were compared with the calculations of Jameson. The results are shown in Figure P7.2.
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