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ONERA M6 Wing Calculations (Single block)

 

The pressure distribution around the ONERA M6 wing at a 3^o 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).

 

Computational Procedure

 

The computational domain employed a block with 189 ´ 40 ´ 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.

 

Obtain the Files

 

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.

Setup file (onera_sb.afl)

Grid file (M6_STD_1B_flat_farfield_189_40_50.grd).

 

Start the Simulation

 

Change the directory to the subfolder with the set up file. Start the simulation by

 

mpirun –np 1 mpiaeroflo.exe < onera_sb.afl

 

 

Results

 

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.

 

 

 

Figure P7.1. Results for the calculations of pressure distribution across the ONERA M6 wing

 

 

The results extracted at the above points were compared with the calculations of Jameson. The results are shown in Figure P7.2.

 

 

 

Figure P7.2. Results for the calculations of pressure distribution across the ONERA M6 wing compared with the calculations of Jameson