Fuselage Surface Pressure Effects due to Wing Interferences
A streamlined fuselage with a rounded cross-sectional area attached with Onera M6 wing was tested using a compressible RANS CFD. Coupled with k-omega SST turbulent model, the craft was tested at 0.8359 Mach which corresponds to 11.72 x 106 Reynolds number. At 3.06˚ wing incidence angle, this simulation is to highlight the fuselage surface pressure variations at the interference region for preliminary aircraft design consideration. By keeping up closely with the physically tested wing through wind tunnel, the results of this simulation can be justified.
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