Reduction of jet noise through use of higher bypass ratios has significantly reduced isolated jet noise and installation effects generally, have become of higher relative importance. Two flight stream velocities for an installed jet engine including pylon and a wing with deployed flap, connected to a fuselage are contrasted. The successful framework developed previously is extended to this challenging configuration. Key flow and noise data are validated against measurements in a blind test. A significant decrease in turbulence kinetic energy levels below the wing and within the shear layer downstream of the flap is found with associated decrease in noise. The authors believe the framework is general enough for inclusion of landing gear and tail-plane.