FOSS provides solutions for CFD problems from low subsonic to supersonic flow regime employing modern clusters including GPU accelerators. As an example, the aerodynamic performance of a fuselage-wing-pylon-nacelle aircraft configuration is studied. The figures that follow present the isentropic Mach number field computed on the aircraft surface for different angles of attack (AoA) and a farfield Mach number of 0.75. A strong shock wave is created on the wing’s suction side as the AoA increases. Red areas have isentropic Mach number higher than 1.0 with the maximum isentropic Mach number on the aircraft, ranging from 1.2 to 1.4 depending on the AoA value.
(a) AoA= -1.5o
(b) AoA = 0.0o
(c) AoA = 1.5o
The skin friction traces over the aircraft surface are also plotted in the next figures. In all cases, a vortical structure, caused by the interaction of the boundary layers of the fuselage and the wing, is created in the wing-fuselage junction close to the wing’s trailing edge. This vortex, fed by the horse-shoe vortex in the wing-fuselage junction at the wing’s leading edge, is getting stronger as the AoA increases. The influence of the shock wave in the skin friction traces is also evident for AoA=0.0o and AoA=1.5o.
(a) AoA= -1.5o
(b) AoA = 0.0o
(c) AoA = 1.5o
The accuracy of the computational results is validated by comparing the computed drag and lift coefficients with the available experimental data. The figure below shows the computed polar curve which is in very good agreement with the experiment.
