Abstract
This study presents a semiempirical model for estimating the acoustic loads generated by a supersonic jet colliding with a rigid perpendicular wall, expanding on traditional methodologies used to assess rocket jet acoustics near the launch structure. Unlike conventional approaches, the proposed model eliminates the need for additional algorithms to describe the flow-surface interaction zone. Instead, it reconfigures acoustic sources attributed to the free jet. Contributions from the undisturbed jet segment, the interaction zone, and acoustic reflection are compared as a function of the nozzle-wall distance. The simulation highlights the dominant role of reconfigured sources in increasing sound levels when the jet interacts with a nearby surface. This methodology is particularly relevant for modeling the acoustic environment during rocket lift-off and can support the engineering design of space vehicles.