Broadband shock-associated noise is a component of jet noise encountered in imperfectly expanded supersonic jets. It is going to be responsible for a dominant part of cabin noise levels at cruise condition for the next-generation commercial aircraft including composite fuselage. A flight simulating facility has been built in the anechoic room of the Centre Acoustique at Ecole Centrale de Lyon and extensive aero-acoustical measurements have been performed to study flight effects on broadband shock-associated noise. In the final paper, flight effects will first be characterized by far field acoustic measurements. In a second step, the main features will be linked to modifications in the jet dynamics due to the secondary stream, with aid of schlieren visualizations, static pressure measurements and particle image velocimetry. The representation of shock-associated noise as the result of an interaction between vortical structures and shocks will be assessed and modelling will be addressed.